CN106240844A - A kind of method for designing of stratospheric airship utricule intensity - Google Patents

Abstract

The invention discloses the method for designing of a kind of stratospheric airship utricule intensity, utilize fundamental strength design theory, utricule strength test statistical data, the theoretical calculation formula of utricule intensity that stratospheric airship utricule Intensity Design formula is derived, determine the design cycle of stratospheric airship utricule intensity on this basis, including: the maximum curvature radius of dirigible utricule is determined according to the General layout Plan of stratospheric airship；Choose suitable Airship Envelope Materials and obtain the intensive parameter of material；General layout Plan according to stratospheric airship determines the expected value of utricule inside and outside differential pressure；Dirigible utricule thickness is determined according to stratospheric airship utricule Intensity Design formula.Compared with prior art, the method can effectively reduce the design error in stratospheric airship utricule strength design theory, improves the reliability of utricule design.

Description

A kind of method for designing of stratospheric airship utricule intensity

Technical field

The present invention relates to aviation aircraft design field, relate more specifically to a kind of stratospheric airship utricule intensity Method for designing.

Background technology

Stratospheric airship is that a kind of dependence is lighter than the gas (such as helium, hydrogen etc.) of air and produces the lift-off of quiet buoyancy, relies on Control system and propulsion system realize pinpointing resident and low-speed maneuver floating class aircraft in stratosphere, have airborne period Length, energy consumption are low, efficiency-cost ratio advantages of higher, are widely used in reconnaissance and surveillance, earth observation, environmental monitoring, emergency disaster relief, scientific exploration The fields such as survey, have significant application value and wide application prospect, have the most become the study hotspot of aviation field.

Stratospheric airship is stayed day and night temperature in null process for a long time and is changed greatly, the phase in the daytime of the buoyant gas in dirigible utricule Between the pressure reduction that caused by temperature rise about between 1300-1600 handkerchief, be about the 25%-30% of the atmospheric gas pressure of degree in outage；It is additionally Prevent the seepage of buoyant gas (helium) in null process from also needing to fill in dirigible utricule and add a certain amount of surplus buoyant gas, Its pressure reduction caused is about 500-2000 handkerchief, is about the 10%-30% of the air pressure of degree in outage.Overlaying influence at both pressure reduction Under, in the sky stop long-term for ensureing stratospheric airship, need to ensure that dirigible utricule has the voltage endurance capability of abundance (to need appropriate design Dirigible utricule intensity), to maintain stablizing of dirigible aerodynamic configuration.

According to stratospheric airship design theory, dirigible utricule intensity depends primarily on maximum curvature radius and the utricule of utricule The strength of materials.But, owing to lacking rational theoretical direction and practical experience, during dirigible utricule Intensity Design theoretical strength with Laboratory strength deviation is bigger, it is impossible to meet engineering practice demand.It is therefore desirable to it is strong to propose a kind of new stratospheric airship utricule The method for designing of degree, to improve the reliability of dirigible utricule design.

Summary of the invention

It is an object of the invention to solve the Intensity Design problem of stratospheric airship utricule, effectively reduce utricule Intensity Design Design error in theory, improves the reliability of dirigible utricule design.

For achieving the above object, the present invention utilizes fundamental strength design theory, utricule strength test statistical data, utricule strong Utricule Intensity Design formula is derived by the theoretical calculation formula of degree, particularly as follows:

$\frac{\[\mathrm{\σ}\]}{K\mathrm{\σ}}=\frac{\mathrm{\λ}\frac{\mathrm{\δ}}{r^{\mathrm{\α}}}}{K\mathrm{\β}pr}=\mathrm{\η}(\mathrm{\λ},K,\mathrm{\β},p)\frac{\mathrm{\δ}}{r^{1+\mathrm{\α}}}=\mathrm{\η}\frac{\mathrm{\δ}}{r^{1+\mathrm{\α}}}\≥1$

Wherein, [σ]-envelop materials allowable stress；σ-envelop materials working stress；K-design safety factor (DSF), value is 3.5；λ-envelop materials Strength co-mputation coefficient；δ-envelop materials thickness；R-utricule maximum curvature radius；α-utricule process ruggedness moves back Change coefficient, survey 0.4 ± 0.2；β-utricule working stress design factor；P-utricule inside and outside differential pressure；η-coefficient of colligation characterizes.

According to above-mentioned theory formula: the maximum curvature radius of dirigible utricule is the biggest, utricule compressive resistance is degenerated the biggest；When flying When the volume of ship utricule increases, the compressive resistance of utricule is affected relatively big by utricule change in volume, with envelop materials thickness or strong The increase and decrease of degree is the most proportional；When dirigible utricule volume is bigger, dirigible utricule intensity is by the shadow of its maximum curvature radius Ringing relatively big, simple rely on envelop materials thickness or the increase of intensity, make that the volume of buoyancy utricule increases is limited in one's ability, even Lose more than gain.In this theoretical basis, it is proposed that a kind of new stratospheric airship utricule strength design, specifically, implement Step includes:

Step one: determine maximum curvature radius r of dirigible utricule according to the General layout Plan of stratospheric airship；

Step 2: choose suitable Airship Envelope Materials, and obtain the intensive parameter [σ] of above-mentioned material；

Step 3: determine the expected value of utricule inside and outside differential pressure p according to the General layout Plan of stratospheric airship；

Step 4: according to formulaDetermine dirigible utricule thickness δ, i.e. meet the capsule of the actual application of stratospheric airship Body thickness.

Compared with prior art, the method determined by theoretical derivation the key affecting stratospheric airship utricule intensity because of Element, and determine each parameter of dirigible utricule its voltage endurance capability affected size, it is to avoid during dirigible utricule Intensity Design The problem that theoretical strength is bigger with laboratory strength deviation, is effectively increased the reliability of dirigible utricule design.

By description below and combine accompanying drawing, the present invention will become more fully apparent, and accompanying drawing is for explaining the reality of the present invention Execute example.

Accompanying drawing explanation

Fig. 1 is stratospheric airship utricule Intensity Design flow chart of the present invention；

Detailed description of the invention

With reference now to accompanying drawing, embodiments of the invention are described.

Refer to Fig. 1, the method for designing of the present invention a kind of stratospheric airship utricule intensity, it is embodied as step and includes:

Step one: determine maximum curvature radius r of dirigible utricule according to the General layout Plan of stratospheric airship；

Step 2: choose suitable Airship Envelope Materials, and obtain the intensive parameter [σ] of above-mentioned material；

Step 3: determine the expected value of utricule inside and outside differential pressure p according to the General layout Plan of stratospheric airship；

Step 4: according to formulaDetermine dirigible utricule thickness δ, i.e. meet the capsule of the actual application of stratospheric airship Body thickness.

Above in association with most preferred embodiment, invention has been described, but the invention is not limited in enforcement disclosed above Example, and amendment, the equivalent combinations that the various essence according to the present invention is carried out should be contained.

Claims (1)

1. the method for designing of a stratospheric airship utricule intensity, it is characterised in that utilize fundamental strength design theory, utricule strong Utricule Intensity Design formula is derived by degree test statistics data, the theoretical calculation formula of utricule intensity, particularly as follows:

$\frac{\[\mathrm{\σ}\]}{K\mathrm{\σ}}=\frac{\mathrm{\λ}\frac{\mathrm{\δ}}{r^{\mathrm{\α}}}}{K\mathrm{\β}pr}=\mathrm{\η}(\mathrm{\λ},K,\mathrm{\β},p)\frac{\mathrm{\δ}}{r^{1+\mathrm{\α}}}=\mathrm{\η}\frac{\mathrm{\δ}}{r^{1+\mathrm{\α}}}\≥1$

Wherein, [σ]-envelop materials allowable stress；σ-envelop materials working stress；K-design safety factor (DSF), value is 3.5；λ- Envelop materials Strength co-mputation coefficient；δ-envelop materials thickness；R-utricule maximum curvature radius；α-utricule process ruggedness degenerate system Number, surveys 0.4 ± 0.2；β-utricule working stress design factor；P-utricule inside and outside differential pressure；η-coefficient of colligation characterizes.

Stratospheric airship utricule Intensity Design, with above-mentioned formula as theoretical foundation, is embodied as step and includes:

Step one: determine maximum curvature radius r of dirigible utricule according to the General layout Plan of stratospheric airship；

Step 2: choose suitable Airship Envelope Materials, and obtain the intensive parameter [σ] of above-mentioned material；

Step 3: determine the expected value of utricule inside and outside differential pressure p according to the General layout Plan of stratospheric airship；

Step 4: according to formulaDetermining dirigible utricule thickness δ, the utricule i.e. meeting the actual application of stratospheric airship is thick Degree.