CN200997733Y

CN200997733Y - Comprehensive recorder casing of plane

Info

Publication number: CN200997733Y
Application number: CN 200720002611
Authority: CN
Inventors: 王云松
Original assignee: STATE-OWNED QIANSHAN ELECTRONIC INSTRUMENTS FACTORY
Current assignee: Shaanxi Qianshan Avionics Co Ltd
Priority date: 2007-01-24
Filing date: 2007-01-24
Publication date: 2007-12-26
Anticipated expiration: 2017-01-24

Abstract

An airplane composite recorder casing is composed of a metal casing, a heat-insulating layer, a heat absorption and damping layer and a seal course and is characterized in that the internal wall of the metal casing is provided with a layer of NM-level silicon oxide and fibrous compound heat-insulating layer, of which the heat-insulating layer is fulfilled with powder inorganic salt heat absorption and damping medium, and the sealing rubber package memory planes are suspended in the heat absorption medium.

Description

Airplane synthetic register housing

Technical field

The utility model relates to a kind of airplane synthetic register housing that is used for aircraft, belongs to the airborne technical field of electronic equipment.

Background technology

The crash survival performance of the anti-crash housing of the original airplane synthetic register of China is followed the airworthiness standard TSO-C51a standard of U.S.'s early sixties promulgation mostly, a statistics according to national transportation safety committee shows, from 1966 to 1993, the ginseng that flies with this standard manufacture 47% is damaged in airplane crash, causes accident analysis to carry out.For this reason, the suggestion FAA of national transportation safety committee cancellation TSO-C51a, and issued that in 1996 " flight data recording system technical stipulation " is TSO-C124a, this standard has proposed more strict examination requirement to flying to join register, fly to join the survival rate of register in airplane crash with raising, new standard is once proposition, and countries in the world fall over each other to adopt on type aircraft.Technical standard order CTSO-C123a and CTSO-C124a that CAAC has issued in 2003 according to this standard are to improve the survival rate of airplane synthetic register in airplane crash.TSO-C51a and the CTSO-C124a standard main distinction on crash survival performance sees Table 1:

Table 1

Sequence number	Pilot project	TSO-C51a	TSO-C124a
Sequence number	Pilot project	TSO-C51a	TSO-C124a	1	High impact shock test	Peak accelerator 〉=1000g duration 〉=5ms surge waveform: half-sine wave applies axially: three quadrature main shafts	Peak accelerator 〉=3400g duration 〉=6.5ms surge waveform: half-sine wave applies axially: from the most fragile direction be applied to the most fragile axially on
2	Anti-penetration test	Weight weight: 227kg hoisting depth: 3.05m punch diameter: φ 6.4mm punch length: 45mm (making by oneself) drift hardness: HRC36-39 casting bed thickness: 1m (making by oneself) housing is placed directly in that penetration power acts on the logger shell on the casting bed	Weight weight: 227kg hoisting depth: 3.05m punch diameter: φ 6.35 ± 0.1mm punch length: 40 ± 1mm drift hardness: HRC39-45 casting bed thickness: the 0.5m housing is placed on the rigidity plate of area 320 * 320, and penetration power acts on the most fragile of logger	1	High impact shock test

		On the crucial face	On dangerous spot on
		On the crucial face	On dangerous spot on	3	Static squeeze test	Static extruding force: 22.25KN applies direction: three quadrature major axes orientation application times: each axial 5min	Static extruding force: 22.25KN applies direction, and three main faces, four diagonal application times: each direction is 5min at least
4	The high temperature bonfire test	Flame temperature: 1100 ℃ of flame encompasses area 〉=50% baked wheaten cake time 〉=30min	Flame temperature: 1100 ℃ of flame encompasses areas: 100% baked wheaten cake time 〉=60min flame minimum thermal flux: 158kw/m ²	3	Static squeeze test
4	The high temperature bonfire test			5	In warm bonfire test	Do not have	260℃，10h
6	The deep sea pressure test	Do not have	Seawater pressure: 60Mpa (6000m deep-sea water depth) the pressurized time: 30 days special circumstances are 24h	5	In warm bonfire test	Do not have	260℃，10h
6	The deep sea pressure test	Do not have		7	The sea water immersion test	Recording medium immerses seawater 36h	Register is dark at 3m, soaks 30 days in the seawater that temperature is 25 ℃
8	The corrosive substance soak test	Do not have	3 kinds of fuel oils, a kind of lubricating oil, a kind of hydraulic oil, a kind of lavatory flushing liquid kind are soaked in 6 kinds of extinguishing chemicals of 48h and are soaked 8h	7	The sea water immersion test	Recording medium immerses seawater 36h

At the at present existing anti-crash housing of airplane synthetic register that satisfies the TSO-C51a standard, be to scribble one deck fire resistant coating mostly at the metal shell external surface, the inner hydrosilicate class material of filling is as thermal insulation layer, there is a metal inner casing thermal insulation layer inside, one element board mount is installed so that the read-only storage plate in metal inner casing inside, the protective casing of this kind structure exists complex process, cost is very high, and under the aircraft airborne environmental condition, use for a long time, outside fire resistant coating moisture-sensitive comes off, moisture thermal insulation layer water evaporates causes the protective casing barrier propterty to descend, drawbacks such as enclosure interior fault rate increase; In addition, when aviation accident is born,, high-octane thump cause the black box safeguard function to lose efficacy owing to easily causing metal inner housing deformed damaged memory plate.

In order to improve the crash survival and the reliability of protective casing, original fire resistant coating, hydrosilicate material, sealing wax, metal inner casing, element board support etc. have been cancelled in the present invention, the shaped design of housing is become cylinder, shell body adopts the novel ultra-high strength steel, with the mixture of novel nano level silicon oxide and fiber as main heat insulation layer, memory plate adopts suspension method installation etc., improved the crash survival performance of protective casing greatly by above-mentioned measure, simplified process structure, reduce cost, improved reliability of products.

Summary of the invention

The purpose of this utility model is: provide a kind of and satisfy the technical standard order CTSO-C123a of CAAC and CTSO-C124a standard and can use reliability height, the anti-crash housing of the simple airplane synthetic register of process structure for a long time under the aircraft airborne environmental condition.

Technical solution of the present utility model is: the anti-crash housing of airplane synthetic register is laminated by metal shell body 1, heat insulation layer 2, heat absorption vibration damping layer 3, sealant 4, metal shell body inwall has the mixture heat insulation layer of one deck nanoscale silica and fiber, heat insulation layer inside is full of pulverous inorganic salts heat absorption damping medium, caulking gum parcel memory plate suspends and is installed in the heat-absorbing medium, and memory printed board 5 lead-in wires are drawn outside by fairlead.This metal shell body can be cylindrical shape.

The utility model has the advantages that: the airworthiness standard CTSO-C123a and the CTSO-C124a of its up-to-date promulgation of crash survival sexual satisfaction office of CAAC.Through test, it can bear air crash, on fire, explode, the thump of issuable 3400g, 6.5ms when dropping into the sea; Can bear the heavy weight of a 227kg that falls from the 3.05m eminence, it is that the cylindrical steel rods of Φ 6.35mm is vertically pounded stamp on the dangerous spot of the most fragile of register housing that a diameter is installed in the bottom; Can bear the static extruding force of a continuous 22.25kN; Withstand temperature is that 1100 ℃ thermal-flame burns 60min at least continuously, and 260 ℃ middle temperature is burnt 10h at least; Can bear in the dark seawater of 3m and seawater that 6000m is dark in soaked respectively 30 days; Can bear in aviation fuel commonly used, soak 48h, in extinguishing chemical commonly used, soak the soiling solution soak test of 8h after, guarantee that recording medium that enclosure interior is deposited does not damage, the information that is write down is not lost, the reliability height provides sound assurance for carrying out accident analysis.

Description of drawings

Fig. 1 is the cross section view of airplane synthetic register housing;

Fig. 2 is the entity decomposing schematic representation of airplane synthetic register housing, and wherein 1 is the metal shell body; 2 is that heat insulation layer 3 is the sealed envelope layer for heat-

sink shell

4, and 5 is memory plane.

Embodiment

The anti-crash housing of this airplane synthetic register is made up of four layers of overcoat: outermost layer is for adopting the shell body 1 of special unimach manufacturing, in order to bear mechanical damage; Sublevel is to adopt the mixture of novel nano level silicon oxide and fiber as main heat insulation layer 2, in order to importing into of intercept heat; The 3rd layer of heat absorption buffer layer 3 that is constituted for the inorganic salts material destroys when preventing that thermal insulation layer is hit and bears at housing and make when burning that cavity temperature is controlled in the certain limit in the housing; The 4th layer is silicon rubber integument 4, is used for sealed storage device printed board 5, prevents that seawater and soiling solution are to the corrosion of printed board and play certain cushioning effect; Memory printed board lead-in wire is drawn outside by fairlead.

Claims

1, a kind of airplane synthetic register housing, formed by metal shell body, heat insulation layer, heat absorption vibration damping layer, sealant, it is characterized in that, described metal shell body inwall has the mixture heat insulation layer of one deck nanoscale silica and fiber, heat insulation layer inside is full of pulverous inorganic salts heat absorption damping medium, and caulking gum parcel memory plate suspends and is installed in the heat-absorbing medium.

2, airplane synthetic register housing according to claim 1 is characterized in that, described metal shell body is a cylindrical shape.