CN204286240U

CN204286240U - A kind of light composite material missile wing structure with near closed hollow ring

Info

Publication number: CN204286240U
Application number: CN201420628195.XU
Authority: CN
Inventors: 李长春; 刘连元; 水涌涛; 杨永刚; 王成华; 赵振平; 刘秀春; 侯保江; 李晓轩
Original assignee: China Academy of Launch Vehicle Technology CALT; Beijing Aerospace Changzheng Aircraft Institute
Current assignee: China Academy of Launch Vehicle Technology CALT; Beijing Aerospace Changzheng Aircraft Institute
Priority date: 2014-10-27
Filing date: 2014-10-27
Publication date: 2015-04-22
Anticipated expiration: 2024-10-27

Abstract

The utility model discloses a kind of light composite material missile wing structure with near closed hollow ring, trough girder listrium and trough girder web are integrally laid on the surrounding end frame of missile wing, I-beam listrium and I-beam web are positioned in missile wing intermediate mesh part, main connection Taper Pipe is positioned at the middle part of the main connection web of missile wing, wrapped up from both sides respectively by half coated one laying, extend on upper and lower trough girder listrium, missile wing skeleton die cavity frp honeycomb filling block carries out polishing and fills, fill with missile wing skeleton die cavity surrounding contact area PMI foam filled block, hot-forming with honeycomb filling low-density heat shield outside missile wing, missile wing outer surface adopts frp honeycomb filling low-density heat shield hot-forming.The missile wing demand fulfillment lighting that the utility model relates to and high bearing capacity two the key technical indexes, and certain anti-heat-insulating capability should be had, reduce the delivery pressure of delivery system with the power thermal environment adapting to the flight of long-time endoatmosphere simultaneously.

Description

A kind of light composite material missile wing structure with near closed hollow ring

Technical field

The utility model relates to a kind of light composite material missile wing structure with near closed hollow ring, belongs to reentry vehicle field.

Background technology

For increasing the lift of reentry vehicle as far as possible on the basis not changing spacecraft delivery system delivery ability, the present invention proposes a kind of ultra-light full composite material missile wing structure with many near closed hollow rings, be arranged on the bomb body of reentry vehicle, the long gliding flight in endoatmosphere can be realized, to improve the maneuverability of aircraft.

Missile wing at present in domestic and international conventional aircraft adopts the additional thermal protective coating of metallic framework covering or anti-heat-barrier material structure mostly, and metal material has excavated totally as the potentiality of main force support structure material, although as lower in material density such as lightweight aluminium lithium alloy, magnesium alloys but chemical characteristic is more active, processing stability and shaping in all there is some problems, and bearing capacity does not have clear superiority, therefore can not become desirable lighting structural material; And the thermal environment problem that missile wing faces only also cannot meet its lighting requirement by increasing anti-insulation thickness, therefore need a kind ofly to take into account lighting and load prevents the design of heating integrated structure as this reentry vehicle missile wing, to meet its special power thermal environment requirement.

Utility model content

Technical problem to be solved in the utility model is: for overcoming the deficiencies in the prior art, solves the difficult problem that reentry vehicle missile wing needs to take into account lighting, high bearing capacity and anti-heat-insulating capability, for reentry vehicle provides lift, improves its maneuverability.

Technical solution of the present utility model is:

A kind of light composite material missile wing structure with near closed hollow ring, comprise trough girder listrium, trough girder web, I-beam listrium, I-beam web, half coated one laying, main connection Taper Pipe, main connection web, low-density heat shield filled by honeycomb, frp honeycomb filling block and PMI foam filled block, wherein trough girder listrium and trough girder web are integrally laid on the surrounding end frame of missile wing, I-beam listrium and I-beam web composition well word anatomical connectivity are in missile wing intermediate mesh part, main connection Taper Pipe is positioned at the middle part of the main connection web of missile wing, wrapped up from both sides respectively by half coated one laying, extend on upper and lower trough girder listrium, missile wing skeleton die cavity frp honeycomb filling block carries out polishing and fills, fill with missile wing skeleton die cavity surrounding contact area PMI foam filled block, hot-forming with honeycomb filling low-density heat shield outside missile wing, missile wing outer surface adopts frp honeycomb filling low-density heat shield hot-forming.

Described trough girder listrium, trough girder web, I-beam listrium, I-beam web, half coated one laying, main connection Taper Pipe, main connection web all adopt T700/ bismaleimide resin composite material.

The laying direction of described trough girder listrium, trough girder web, I-beam listrium, I-beam web and main connection web is 0 ° and 45 ° of alternately windings, and number of plies ratio is 6.5:3.5.

Half coated one laying and main connection Taper Pipe laying direction are 0 ° and 45 ° and are alternately wound around, and number of plies ratio is 6:4.

The utility model advantage is compared with prior art:

The missile wing demand fulfillment lighting that the utility model relates to and high bearing capacity two the key technical indexes, and certain anti-heat-insulating capability should be had, reduce the delivery pressure of delivery system with the power thermal environment adapting to the flight of long-time endoatmosphere simultaneously.

Accompanying drawing explanation

Fig. 1 is structural representation of the present utility model;

Fig. 2 is that the A-A of Fig. 1 is to sectional view.

Detailed description of the invention

Below in conjunction with accompanying drawing, the utility model is described in detail.

As Fig. 1, shown in 2, a kind of light composite material missile wing structure with near closed hollow ring, comprise trough girder listrium 1, trough girder web 2, I-beam listrium 3, I-beam web 4, half coated one laying 5, main connection Taper Pipe 6, main connection web 7, low-density heat shield 8 filled by honeycomb, frp honeycomb filling block 9 and PMI foam filled block 10, wherein trough girder listrium 1 and trough girder web 2 are integrally laid on the surrounding end frame of missile wing, I-beam listrium 3 and I-beam web 4 are positioned in missile wing intermediate mesh part, main connection Taper Pipe 6 connects with the main middle part being connected web 7 of missile wing, wrapped up from both sides respectively by half coated one laying 5, extend on upper and lower trough girder listrium 1, missile wing skeleton die cavity frp honeycomb filling block 9 carries out polishing and fills, fill with missile wing skeleton die cavity surrounding contact area PMI foam filled block 10, hot-forming with honeycomb filling low-density heat shield 8 outside missile wing, missile wing outer surface adopts frp honeycomb filling low-density heat shield 8 hot-forming.

Described trough girder listrium 1, trough girder web 2, I-beam listrium 3, the coated one laying 5 of I-beam web 4, half, main connection Taper Pipe 6, main connection web 7 all adopt T700/ bismaleimide resin composite material.

The laying direction of described trough girder listrium 1, trough girder web 2, I-beam listrium 3, I-beam web 4 and main connection web 7 is 0 ° and 45 ° and is alternately wound around, and number of plies ratio is 6.5:3.5.

Half coated one laying 5 and main connection Taper Pipe 6 laying direction are 0 ° and 45 ° and are alternately wound around, and number of plies ratio is 6:4.

The utility model applies to the lightweight bearing structure that I-beam, trough girder and Taper Pipe etc. are classical in the design of missile wing, alleviates the weight of missile wing from design feature; By the Lay up design optimization to carbon fibre composite, give full play to the advantage of composite designability, improve the bearing capacity of composite unit volume, demonstrate this effect by finite element analysis and calculating; Select the T700/ bismaleimide resin composite material of lightening fire resistant as missile wing primary load bearing material, solve a difficult problem for missile wing lighting from source; Improve integral rigidity and the heat-proof quality of aerofoil by less weight (accounting for missile wing gross weight 12%), effectively prevent the strength failure that missile wing inner chamber overlapping regions is brought due to defective workmanship; (density is about 0.5g/cm to adopt the honeycomb being applicable to low-to-medium altitude ablation environment to fill the anti-heat-barrier material of low-density ³), (density is about 1.8g/cm with traditional quartz phenolic material ³) compare the heat shield weight that reduce further missile wing.

By to the finite element analysis of missile wing intensity and slow test, the missile wing testpieces (size is about 1000mm × 185mm × 258mm) that the utility model relates to reaches the technical indicator that weight is no more than 16kg, bearing capacity is not less than 4.8t, achieves the breakthrough of ultra-light full composite material missile wing in designing technique and moulding process.

The all form touch positions of the utility model all bond together.

Missile wing forming method can adopt negative and positive shaping to mould one hot-press solidifying, is arranged on reentry vehicle, for aircraft provides lift, generally should uses in pairs by described main connection Taper Pipe 6.

The unexposed technology of the utility model belongs to general knowledge as well known to those skilled in the art.

Claims

1. one kind has the light composite material missile wing structure of near closed hollow ring, it is characterized in that, comprise trough girder listrium (1), trough girder web (2), I-beam listrium (3), I-beam web (4), half coated one laying (5), main connection Taper Pipe (6), main connection web (7), low-density heat shield (8) filled by honeycomb, frp honeycomb filling block (9) and PMI foam filled block (10), wherein trough girder listrium (1) and trough girder web (2) are integrally laid on the surrounding end frame of missile wing, I-beam listrium (3) and I-beam web (4) composition well word anatomical connectivity are in missile wing intermediate mesh part, main connection Taper Pipe (6) connects with the main middle part being connected web (7) of missile wing, and wrapped up from both sides respectively by half coated one laying (5), extend on upper and lower trough girder listrium (1), missile wing skeleton die cavity frp honeycomb filling block (9) is filled after polishing, fill with missile wing skeleton die cavity surrounding contact area PMI foam filled block (10), hot-forming with honeycomb filling low-density heat shield (8) outside missile wing.

2. a kind of light composite material missile wing structure with near closed hollow ring as claimed in claim 1, it is characterized in that, described trough girder listrium (1), trough girder web (2), I-beam listrium (3), I-beam web (4), half coated one laying (5), main connection Taper Pipe (6), main connection web (7) all adopt T700/ bismaleimide resin composite material.

3. a kind of light composite material missile wing structure with near closed hollow ring as claimed in claim 1, it is characterized in that, the laying direction of described trough girder listrium (1), trough girder web (2), I-beam listrium (3), I-beam web (4) and main connection web (7) is 0 ° and 45 ° of alternately windings, and number of plies ratio is 6.5:3.5.

4. a kind of light composite material missile wing structure with near closed hollow ring as claimed in claim 1, it is characterized in that, half coated one laying (5) and main connection Taper Pipe (6) laying direction are 0 ° and 45 ° and are alternately wound around, and number of plies ratio is 6:4.