CN105184894A - High-energy and strong-impact resistant crash protection element protection method - Google Patents
High-energy and strong-impact resistant crash protection element protection method Download PDFInfo
- Publication number
- CN105184894A CN105184894A CN201510464944.9A CN201510464944A CN105184894A CN 105184894 A CN105184894 A CN 105184894A CN 201510464944 A CN201510464944 A CN 201510464944A CN 105184894 A CN105184894 A CN 105184894A
- Authority
- CN
- China
- Prior art keywords
- inner sleeve
- crash
- protection
- rigidity
- rigid
- 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
Landscapes
- Aiming, Guidance, Guns With A Light Source, Armor, Camouflage, And Targets (AREA)
- Buildings Adapted To Withstand Abnormal External Influences (AREA)
Abstract
The invention relates to a high-energy and strong-impact resistant crash protection element protection method and belongs to the aviation airborne electronic device technology field. The provided method employs a double-layer rigid structure protection method. An inner sleeve rigid box element is fixed in a rigid housing in a non-grid manner, thermal protection materials are loaded between two rigid protection layers, and a storage module is loaded in thermal protection materials or non-metal buffer materials in the inner sleeve rigid box. The protection method can meet present up-to-date civil aviation technical standard orders (TSO) crash survival requirements, and more, the strong impact resistance is raised greatly, and strong impact during airplane high-speed (supersonic speed) crash can be borne well. A crash protection element employing the protection method passes TSO-C124b/C123b crash survival sequence test, and the strong impact magnitude is not less than half-sine wave impact energy in 5100g/5ms. The crash protection element passes the ultrasonic speed collision test. User requirements are met.
Description
Technical field
The anti-high-energy thump of the technology of the present invention crashes and protects assembly means of defence to belong to airborne technical field of electronic equipment.
Background technology
The protection assembly that crashes is the core component of flight recorder, and during air crash, have to resist and ruin function, especially resisting strong impact destroys function.Along with improving constantly of aeroplane performance; at present; will the look for novelty flight recorder that grinds of user requires simultaneously, to ensure that it is when the born accident of aircraft high speed meeting civil aviaton's technical standard (TSO), and the crash in flight recorder protects assembly can resist high magnitude thump and survive.Namely require to crash protection assembly with the stroke speed of 340 ~ 370m/s, impact specific target body, and impact acceleration is survived after being not less than the high-magnitude strong-impact test of 15000g.This requirement, far above the thump requirement in the TSO standard that current flight register is followed, that is, flight recorder can bear peak accelerator and be not less than 3400g, action time is not less than 6.5ms, and impact velocity variable quantity is not less than the half-sine wave impact energy of 138m/s.Therefore, the single flight recorder by thump requirement development in civil aviaton's technical standard (TSO) crashes and protects assembly to be not suitable with the new demand of user.
Based on above situation, carry out the research of anti-high magnitude thump crash protection assembly means of defence.It not only compensate for the protection assembly that crashes only can meet crash survival requirement in TSO standard, has also possessed the anti-high magnitude thump safeguard function of aircraft in (supersonic speed) accident situation at a high speed simultaneously.
Summary of the invention
The object of the invention: this invention; the protection assembly that crashes not only meets with the stroke speed of 340 ~ 370m/s; impact specific target body; the requirement and impact acceleration is survived after being not less than the high-magnitude strong-impact test of 15000g, but also to meet civil aviaton technical standard order TS0-C123b and TSO-C124b the test of crash survivor sequence (thump, penetrate, static extruding, high temperature is burnt, low temperature is burnt, corrosive substance soaks, deep sea pressure and sea water immersion test) requirement.
Technical solution of the present invention: anti-high magnitude thump crashes and protects assembly means of defence, the process employs multilayer proofing structure, this structure comprises outer stiff case, the little case assembly of inner sleeve rigidity and thermally protective materials, the little case assembly of inner sleeve rigidity comprises inner sleeve stiff case, storage medium and filling thermally protective materials, inner sleeve stiff case is threaded connection by inner sleeve rigidity lower house and cover plate and forms, and storage medium is made up of memory module and buffering silicon rubber; It is characterized in that,
The process employs double-layer rigid structural shielding method;
Be filled with thermally protective materials between outer rigid housing body and the little case assembly of inner sleeve rigidity, the little case assembly of inner sleeve rigidity is fixed in nonmetal heating protective materials by the non-rigid manner connected without metal;
The little case assembly of inner sleeve rigidity have employed storage medium non-rigid manner and is fixed in thermal protection material or nonmetal padded coaming;
Inner sleeve stiff case have employed the metal material with high strength, high tenacity mechanical characteristic, and its rigidity lower house and cover plate have employed thread connecting mode, and opens storage medium line outlet at lower house and side, cover plate combination termination place;
Memory module is potted in buffering silicon rubber.
Beneficial effect of the present invention:
Use the crash protection assembly of this means of defence not only by the test of TSO-C124b/C123b crash survivor sequence, wherein thump value is not less than the half-sine wave impact energy of 5100g/5ms; And have passed ultrasonic impact test, meet user's requirement, be applicable to equipment military secret and civil aircraft.
Accompanying drawing explanation
Fig. 1 is anti-high magnitude thump crash protection assembly means of defence schematic diagram;
1 is anti-high magnitude thump crash protection assembly; 1-01 is outer stiff case unit; 1-02 is inner sleeve rigidity capsule assembly unit; 1-03 is thermally protective materials unit; 1-02-01 is inner sleeve stiff case unit; 1-02-02 is thermally protective materials or nonmetal padded coaming; 1-02-03 is storage medium unit.
Fig. 2 is the little case assembly schematic diagram of inner sleeve rigidity;
1-02 is the little case assembly of inner sleeve rigidity; Be that storage medium unit forms by 1-02-01 inner sleeve stiff case unit, 1-02-02 thermally protective materials or nonmetal padded coaming unit and 1-02-03.
Fig. 3 is inner sleeve stiff case schematic diagram;
1-02-01 is inner sleeve stiff case; Be made up of 1-02-01-01 inner sleeve rigidity lower housing unit and 1-02-01-02 cover plate unit.
Fig. 4 is storage medium schematic diagram;
1-02-02 is storage medium; Cushion silicon rubber unit by 1-02-02-01 memory module unit and 1-02-02-02 to form.
Embodiment
The principle of the invention
This method have employed double-layer rigid structural shielding method.It is fixed in outer rigid housing body by the little case assembly of inner sleeve rigidity is non-rigid, is namely filled with thermally protective materials between double-layer rigid protection, and memory module is filled in thermally protective materials or nonmetal padded coaming in inner sleeve rigidity capsule.This means of defence not only can meet current up-to-date civil aviaton's technical standard (TSO) crash survival requirement, the more important thing is and to be greatly improved in resisting strong impact ability, better can bear the thump that aircraft is suffered when (supersonic speed) crashes at a high speed.Use the crash protection assembly of this means of defence not only by the test of TSO-C124b/C123b crash survivor sequence, wherein thump value is not less than the half-sine wave impact energy of 5100g/5ms; And have passed ultrasonic impact test.Meet user's requirement.
Anti-high magnitude thump means of defence need possess the feature of following two aspects: one is; be not less than under thump index (as 3400g/6.5ms or 5100g/5ms or the 6000g/5ms) requirement specified in sequential test; register crashes and protects assembly not allow rupture failure or large deformation occur; otherwise can affect and follow-up anti-ly ruin sequential test, especially bonfire test.
Two are, as the anti-high magnitude thump examination of individual event that user requires, allow part operator guards generation large deformation or rupture failure, but the storage medium of its inside (flash chip) are intact.Require and protection feature for above,
Content of the present invention mainly comprises following content.
Shown in following Fig. 1 and Fig. 2, this means of defence have employed double-layer rigid safeguard structure, the i.e. little case assembly of outer stiff case (1-01) inner sleeve rigidity (1-02), and outside between stiff case (1-01) and the little case assembly of inner sleeve rigidity (1-02), be filled with thermally protective materials (1-03).This structure can withstand shocks stress better, and compare single layer rigid safeguard structure, its resisting strong impact limit capacity improves about 3 times.
The little case assembly of inner sleeve rigidity (1-02) is made up of inner sleeve stiff case (1-02-01), storage medium (1-02-02) and filling thermally protective materials (or nonmetal padded coaming) (1-02-03).Effectively protect storage medium (1-02-02) from the destruction of high temperature load and shock load by the thermally protective materials (or nonmetal padded coaming) of double-layer rigid structure and filling.Compare single layer rigid safeguard structure, adding inner sleeve stiff case (1-02-01) is the key factor improving protection assembly resisting strong impact limit capacity of crashing.
The crash protection assembly that patent of the present invention is introduced forms primarily of double-layer rigid housing unit (1-01 and 1-02), thermally protective materials (1-03,1-02-03) or nonmetal padded coaming (1-02-03).
Embodiment
Anti-high magnitude thump crashes and protects the means of defence of assembly; to make structure exactly under the prerequisite of minimum weight (or material) and volume cost; possess above-mentioned two described aspect means of defence features; not only make crash protect modular construction regulation load effect under distortion or rupture failure controlled; simultaneously; improve the impact failure limit of structure as far as possible, make its operator guards in limiting damage condition, absorption impact energy that only may be many.Therefore, its solution is as follows:
1. the shell body (1-01) in double-layer rigid housing, absorbs the energy of output in impact process mainly through the controllable deforming of its structure or rupture failure, slacken the destruction of impacting the protection assembly that to crash to entirety.It requires the large deformation not allowing rupture failure to occur or affects follow-up test in sequential test; Under the high-speed impact working condition that similar user requires, allow large deformation or rupture failure occur.Therefore, shell body adopts and has high strength, the Steel material of high tenacity mechanical property feature or titanium alloy material; Forming method adopts one machine-shaping, and shape adopts U-shaped, cylindrical, spherical or band Rouno Cormer Pregrinding Wheel transition square structure, and the design feature of this programme have employed U-shaped structure.
2. the little case assembly of inner sleeve (1-02) in double-layer rigid housing; its effect is; shell body (1-01) is under high magnitude impact loading; if there is large deformation or rupture failure; protect the storage medium (1-02-02) of its inside by inner sleeve stiff case (1-02-01) further, avoid the destruction directly suffering external applied load.Therefore, in rigidity, set of shells does not allow the destruction (fracture or large deformation) occurring affect internal storage medium under Strong Impact Loading effect, and stiff case employing has high strength, the Steel material of high tenacity mechanical property feature or titanium alloy material; Forming method adopts one machine-shaping, and shape adopts U-shaped, cylindrical, spherical or band Rouno Cormer Pregrinding Wheel transition square structure.The design feature of this programme as shown in Figure 2 and Figure 3, have employed the U-shaped structure similar to shell body, inner sleeve stiff case (1-02-01) is made up of inner sleeve rigidity lower house (1-02-01-01) and cover plate (1-02-01-02), lower house have employed with the connection of cover plate and is threaded, and opens storage medium line outlet at lower house and side, cover plate combination termination place.Namely this structure ensure that the overall stiffness requirement of interior set of shells, solves again storage medium outlet assembly problem.
3., as Fig. 1 and Fig. 2 is filled with thermally protective materials (1-03) between double-layer rigid protective casing, the little case assembly of inner sleeve is non-rigid to be fixed in thermally protective materials (1-03); Thermally protective materials or nonmetal padded coaming (1-02-03) is filled between inner sleeve stiff case (1-02-01) and storage medium (1-02-02); High temperature resistance after namely this design feature solves the protection assembly thump that crashes destroys problem; solve again interior set of shells and be connected (nonmetal connection) problem with the non-rigid of shell body; delay and slacken in impact process; the destruction of the internal set of shells of impulsive force, protects storage medium further.
As shown in Figure 4, storage medium is made up of memory module and buffering silicon rubber block, and memory module is potted in buffering silicon rubber, delays and slackens the destruction of impulsive force to memory module.
Claims (1)
1. anti-high-energy thump crashes and protects assembly means of defence, the process employs multilayer proofing structure, this structure comprises outer stiff case, the little case assembly of inner sleeve rigidity and thermally protective materials, the little case assembly of inner sleeve rigidity comprises inner sleeve stiff case, storage medium and filling thermally protective materials, inner sleeve stiff case is threaded connection by inner sleeve rigidity lower house and cover plate and forms, and storage medium is made up of memory module and buffering silicon rubber; It is characterized in that,
The process employs double-layer rigid structural shielding method;
Be filled with thermally protective materials between outer rigid housing body and the little case assembly of inner sleeve rigidity, the little case assembly of inner sleeve rigidity is fixed in nonmetal heating protective materials by the non-rigid manner connected without metal;
The little case assembly of inner sleeve rigidity have employed storage medium non-rigid manner and is fixed in thermal protection material or nonmetal padded coaming;
Inner sleeve stiff case have employed the metal material with high strength, high tenacity mechanical characteristic, and its rigidity lower house and cover plate have employed thread connecting mode, and opens storage medium line outlet at lower house and side, cover plate combination termination place;
Memory module is potted in buffering silicon rubber.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201510464944.9A CN105184894A (en) | 2015-07-31 | 2015-07-31 | High-energy and strong-impact resistant crash protection element protection method |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201510464944.9A CN105184894A (en) | 2015-07-31 | 2015-07-31 | High-energy and strong-impact resistant crash protection element protection method |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN105184894A true CN105184894A (en) | 2015-12-23 |
Family
ID=54906943
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201510464944.9A Pending CN105184894A (en) | 2015-07-31 | 2015-07-31 | High-energy and strong-impact resistant crash protection element protection method |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN105184894A (en) |
Cited By (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN105957186A (en) * | 2016-05-20 | 2016-09-21 | 成都凯天电子股份有限公司 | Method for potting flight parameter recorder storage unit with silicone rubber |
| CN106228636A (en) * | 2016-07-15 | 2016-12-14 | 航天材料及工艺研究所 | A kind of flight data recor der thermal protection structure |
| CN107764497A (en) * | 2017-09-13 | 2018-03-06 | 陕西千山航空电子有限责任公司 | A kind of shock loading wirelessly stores test device |
| CN110809378A (en) * | 2019-10-23 | 2020-02-18 | 航天材料及工艺研究所 | Damping/heat insulation structure and preparation method and application thereof |
| CN111591464A (en) * | 2020-03-31 | 2020-08-28 | 上海卫星工程研究所 | Deep space impactor and impact protection performance evaluation method thereof |
| CN113466894A (en) * | 2021-06-09 | 2021-10-01 | 航天恒星科技有限公司 | Protection system of emergency positioning transmitter |
| CN115620425A (en) * | 2022-12-08 | 2023-01-17 | 湖南高至科技有限公司 | High-overload aircraft recorder |
Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN2579800Y (en) * | 2002-06-26 | 2003-10-15 | 刘日新 | High temperature insulation structure for data recorder for ship |
| CN2764716Y (en) * | 2005-05-31 | 2006-03-15 | 魏法军 | Data protection unit for ship |
| CN200997733Y (en) * | 2007-01-24 | 2007-12-26 | 国营千山电子仪器厂 | Comprehensive recorder casing of plane |
| EP2150097B1 (en) * | 2008-07-31 | 2012-09-12 | GE Aviation Systems LLC | Method and apparatus for electrical component physical protection |
| CN103035045A (en) * | 2012-12-24 | 2013-04-10 | 江苏海兰船舶电气***科技有限公司 | Ship data protection unit |
| CN103582356A (en) * | 2012-07-18 | 2014-02-12 | 霍尼韦尔国际公司 | Systems and methods for protecting a flight recorder |
-
2015
- 2015-07-31 CN CN201510464944.9A patent/CN105184894A/en active Pending
Patent Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN2579800Y (en) * | 2002-06-26 | 2003-10-15 | 刘日新 | High temperature insulation structure for data recorder for ship |
| CN2764716Y (en) * | 2005-05-31 | 2006-03-15 | 魏法军 | Data protection unit for ship |
| CN200997733Y (en) * | 2007-01-24 | 2007-12-26 | 国营千山电子仪器厂 | Comprehensive recorder casing of plane |
| EP2150097B1 (en) * | 2008-07-31 | 2012-09-12 | GE Aviation Systems LLC | Method and apparatus for electrical component physical protection |
| CN103582356A (en) * | 2012-07-18 | 2014-02-12 | 霍尼韦尔国际公司 | Systems and methods for protecting a flight recorder |
| CN103035045A (en) * | 2012-12-24 | 2013-04-10 | 江苏海兰船舶电气***科技有限公司 | Ship data protection unit |
Cited By (10)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN105957186A (en) * | 2016-05-20 | 2016-09-21 | 成都凯天电子股份有限公司 | Method for potting flight parameter recorder storage unit with silicone rubber |
| CN106228636A (en) * | 2016-07-15 | 2016-12-14 | 航天材料及工艺研究所 | A kind of flight data recor der thermal protection structure |
| CN106228636B (en) * | 2016-07-15 | 2018-04-10 | 航天材料及工艺研究所 | A kind of flight data recor der thermal protection structure |
| CN107764497A (en) * | 2017-09-13 | 2018-03-06 | 陕西千山航空电子有限责任公司 | A kind of shock loading wirelessly stores test device |
| CN107764497B (en) * | 2017-09-13 | 2019-11-15 | 陕西千山航空电子有限责任公司 | A kind of shock loading wirelessly stores test device |
| CN110809378A (en) * | 2019-10-23 | 2020-02-18 | 航天材料及工艺研究所 | Damping/heat insulation structure and preparation method and application thereof |
| CN111591464A (en) * | 2020-03-31 | 2020-08-28 | 上海卫星工程研究所 | Deep space impactor and impact protection performance evaluation method thereof |
| CN113466894A (en) * | 2021-06-09 | 2021-10-01 | 航天恒星科技有限公司 | Protection system of emergency positioning transmitter |
| CN115620425A (en) * | 2022-12-08 | 2023-01-17 | 湖南高至科技有限公司 | High-overload aircraft recorder |
| CN115620425B (en) * | 2022-12-08 | 2023-04-28 | 湖南高至科技有限公司 | High overload aircraft recorder |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| CN105184894A (en) | High-energy and strong-impact resistant crash protection element protection method | |
| CN112413038B (en) | Composite load reduction device for high-speed water entry of navigation body | |
| JP6707117B2 (en) | Blast/shock frequency tuning and mitigation | |
| CN205608828U (en) | Flight data record protection memory excels in | |
| Ding et al. | Blast alleviation of cellular sacrificial cladding: a nonlinear plastic shock model | |
| CN104553143A (en) | Novel explosion-proof composite structure based on metamaterial | |
| CN109860455A (en) | A kind of power battery safety device | |
| CN113650374B (en) | Ship side flexible anti-fragment penetration layer and manufacturing method thereof | |
| CN107658030A (en) | A kind of ECC ripples filling reactor shock resistance shielding water jacket | |
| CN106881921A (en) | Shock wave composite energy dissipation protector | |
| CN115071880B (en) | Built-in energy-absorbing type combined load reduction structure and method for high-speed water entry of aircraft | |
| CN104736368A (en) | Tank resistant to the overpressures caused by projectile impact | |
| CN203904918U (en) | Two-stage anti-collision buffer ring | |
| CN109268429A (en) | A kind of non-concatenated simple and reliable whole star damper | |
| Jha et al. | Bird strike damage and analysis of UAV’s airframe | |
| Iliescu et al. | Satellites-spacecraft materials and hypervelocity impact (HVI) testing: Numerical simulations | |
| Al-Rifaie | Novel energy-absorbing auxetic sandwich panel with detached corrugated aluminium layers | |
| Patel et al. | Dynamic Response Comparison of Sandwich Panels with Honeycomb and Foam Core Under Blast Loads: A Quantitative Study | |
| CN113752647B (en) | Sensor protection device for real ship target shooting test | |
| Ryan et al. | Development of the next generation of meteoroid and orbital debris shields | |
| CAI et al. | Simulation of non-penetrating damage of head due to bullet impact to helmet | |
| Zhang et al. | Advancements in research on high-overload impact-buffering protective materials | |
| Yamada et al. | High-speed compact entry capsule enhanced by lightweight ablator and crushable structure | |
| Zhang et al. | A Comparative Study on Impact Resistance of Composite Buffer Ring Structures Under Double Impact Loading | |
| CN114267097A (en) | Cell filling type multilayer ball structure and data recorder |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| C06 | Publication | ||
| PB01 | Publication | ||
| C10 | Entry into substantive examination | ||
| SE01 | Entry into force of request for substantive examination | ||
| WD01 | Invention patent application deemed withdrawn after publication |
Application publication date: 20151223 |
|
| WD01 | Invention patent application deemed withdrawn after publication |