CN110626519A - Aircraft surface defect scale control method for reducing influence on flow transition - Google Patents

Aircraft surface defect scale control method for reducing influence on flow transition Download PDF

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Publication number
CN110626519A
CN110626519A CN201910791669.XA CN201910791669A CN110626519A CN 110626519 A CN110626519 A CN 110626519A CN 201910791669 A CN201910791669 A CN 201910791669A CN 110626519 A CN110626519 A CN 110626519A
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aircraft
defect
scale
transition
defect scale
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CN110626519B (en
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李宇
聂亮
刘国仟
周禹
王迅
袁野
聂春生
刘宇飞
张宏宇
董耀军
常园园
杨攀
陈敏
赵晓利
朱广生
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China Academy of Launch Vehicle Technology CALT
Beijing Institute of Near Space Vehicles System Engineering
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China Academy of Launch Vehicle Technology CALT
Beijing Institute of Near Space Vehicles System Engineering
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    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64F—GROUND OR AIRCRAFT-CARRIER-DECK INSTALLATIONS SPECIALLY ADAPTED FOR USE IN CONNECTION WITH AIRCRAFT; DESIGNING, MANUFACTURING, ASSEMBLING, CLEANING, MAINTAINING OR REPAIRING AIRCRAFT, NOT OTHERWISE PROVIDED FOR; HANDLING, TRANSPORTING, TESTING OR INSPECTING AIRCRAFT COMPONENTS, NOT OTHERWISE PROVIDED FOR
    • B64F5/00—Designing, manufacturing, assembling, cleaning, maintaining or repairing aircraft, not otherwise provided for; Handling, transporting, testing or inspecting aircraft components, not otherwise provided for
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64F—GROUND OR AIRCRAFT-CARRIER-DECK INSTALLATIONS SPECIALLY ADAPTED FOR USE IN CONNECTION WITH AIRCRAFT; DESIGNING, MANUFACTURING, ASSEMBLING, CLEANING, MAINTAINING OR REPAIRING AIRCRAFT, NOT OTHERWISE PROVIDED FOR; HANDLING, TRANSPORTING, TESTING OR INSPECTING AIRCRAFT COMPONENTS, NOT OTHERWISE PROVIDED FOR
    • B64F5/00—Designing, manufacturing, assembling, cleaning, maintaining or repairing aircraft, not otherwise provided for; Handling, transporting, testing or inspecting aircraft components, not otherwise provided for
    • B64F5/60—Testing or inspecting aircraft components or systems
    • G—PHYSICS
    • G01—MEASURING; TESTING
    • G01M—TESTING STATIC OR DYNAMIC BALANCE OF MACHINES OR STRUCTURES; TESTING OF STRUCTURES OR APPARATUS, NOT OTHERWISE PROVIDED FOR
    • G01M9/00—Aerodynamic testing; Arrangements in or on wind tunnels
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64C—AEROPLANES; HELICOPTERS
    • B64C30/00—Supersonic type aircraft

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  • Engineering & Computer Science (AREA)
  • Manufacturing & Machinery (AREA)
  • Transportation (AREA)
  • Aviation & Aerospace Engineering (AREA)
  • Physics & Mathematics (AREA)
  • Fluid Mechanics (AREA)
  • General Physics & Mathematics (AREA)
  • Aerodynamic Tests, Hydrodynamic Tests, Wind Tunnels, And Water Tanks (AREA)

Abstract

The invention provides an aircraft surface defect scale control method for reducing the influence on flow transition, which comprises the steps of firstly carrying out flow transition research on an aircraft by using a theoretical analysis means or a ground test means to obtain a constraint range of a surface defect scale meeting the condition that the transition of a boundary layer is not influenced; then, performing combined simulation analysis of pneumatic heating, a structural temperature field and a deformation field on the section with the defect, and extracting thermal deformation data of each section with the defect in the flight process from the structural deformation calculation result; and finally, designing the initial defect scale to be processed according to the constraint range and the thermal deformation data by utilizing a strategy of counteracting the thermal deformation by the initial defect scale, and ensuring that the actual defect scale meets the constraint range in the flight process. The method can reasonably and effectively control the surface defect scale of the aircraft, reduce the possibility of inducing surface transition, and ensure the reliable work of the thermal protection system of the aircraft.

Description

Aircraft surface defect scale control method for reducing influence on flow transition
Technical Field
The invention relates to an aircraft surface defect scale control method for reducing the transition influence on flow, which is suitable for controlling the defect scales of a surface cabin section butt joint step or gap, a step, gap or recess formed by antenna window installation, a bulge or recess formed by sensor installation and the like in a hypersonic aircraft flight test so as to reduce the influence on the transition of the hypersonic aircraft surface flow, and belongs to the technical field of transition of hypersonic aircraft.
Background
The hypersonic aircraft spans a wider flight airspace and a wider speed domain, and the surface flow of the hypersonic aircraft can generate boundary layer transition along with the increase of the Reynolds number of the incoming flow. Because the wall friction coefficient/heat exchange coefficient of the laminar boundary layer and the turbulent boundary layer are obviously different, the boundary layer transition has obvious influence on the aerodynamic force of the surface of the aircraft, particularly the aerodynamic heat distribution. In the transition propulsion process, the aerodynamic and control characteristics of the aircraft are obviously changed, the surface heat flow is increased rapidly after the transition occurs, and the turbulent heating is 3-5 times that of the laminar heating in a typical hypersonic speed state. Therefore, the boundary layer transition is an important factor that must be considered in the design of the hypersonic aircraft.
The hypersonic speed boundary layer transition is a complex flow phenomenon, the mechanism is complex, the influencing factors are numerous, and the factors influencing the transition mainly include three aspects: the profile of the aircraft itself, the flight state, and the surface state of the aircraft. The influence of the profile of the aircraft itself includes aircraft head curvature, surface profile curvature, surface steps, gaps, local protrusions/depressions, and the like. The surface local defects such as steps, gaps and local bulges/recesses (such as antenna window installation and sensor installation) formed by butt joint of cabin sections inevitably exist in the processing, manufacturing and assembling processes of the aircraft, the surface local defects with overlarge sizes can generate obvious disturbance on local flow, the transition of a boundary layer is induced in advance, the aerodynamic heating of the surface of the aircraft becomes severer, and the reliable operation of a thermal protection system of the aircraft is obviously influenced. Therefore, it is necessary to control the scale of the surface defect of the aircraft, so as to reduce the possibility of transition and improve the working reliability of the thermal protection system.
At present, no mature method for controlling the surface defect size of the aircraft to reduce the transition influence of the aircraft exists, and the defect size of surface steps, gaps and the like is maintained at a smaller value (for example, 0.2mm) mainly through the process control of processing, manufacturing and assembling links in engineering development. In practical engineering application, however, the method has some defects, and cannot completely meet the requirement of surface transition control of the aircraft on the surface defect scale. On the one hand, the constraint range of defect scales such as surface steps and gaps which are not influenced by surface transition of the aircraft is possibly strict, the constraint range is influenced by the processing, manufacturing and assembling process level, and especially for composite materials, the existing process level can not ensure that the dimensions such as the steps and the gaps can meet the constraint range. On the other hand, due to the fact that materials and sizes of all sections generating the steps and the gaps are different, thermal response of all parts is also different after the parts are subjected to pneumatic heating in the actual flying process, thermal deformation of all the sections is different, the dimensions of the initial steps, the gaps and the like can be changed, and therefore the defect dimension can not meet the constraint range. Therefore, the defect scales such as surface steps, gaps and the like of the aircraft are difficult to control reasonably, and the possibility of inducing forward transition to endanger the reliable work of the thermal protection system is increased.
Disclosure of Invention
The technical problem to be solved by the invention is as follows: the method for controlling the surface defect scale of the aircraft can reasonably and effectively control the surface defect scale of the aircraft, reduce the possibility of inducing surface transition and ensure the reliable work of a thermal protection system of the aircraft.
The technical solution of the invention is as follows:
an aircraft surface defect scale control method for reducing the influence on flow transition comprises the following steps:
(1) carrying out flow transition research on the aircraft by using a theoretical analysis means or a ground test means to obtain a constraint range of a surface defect scale which meets the requirement that the transition of the boundary layer is not influenced;
(2) performing pneumatic heating analysis on the aircraft to obtain the surface heat flow distribution of the aircraft, performing combined simulation analysis on a structural temperature field and a deformation field of the aircraft by taking the surface heat flow distribution of the aircraft as input, and extracting thermal deformation data of each section generating defects in the flight process from the structural deformation calculation result;
(3) and (3) designing the initial defect scale to be processed according to the constraint range and the thermal deformation data obtained in the steps (1) and (2) by utilizing a strategy of counteracting the thermal deformation by utilizing the initial defect scale, and ensuring that the actual defect scale in the flight process meets the constraint range.
In the step (1), the constraint range of the defect scale is characterized in that the ratio | h/δ | of the defect scale h to the boundary layer thickness δ of the position where the defect is located is smaller than a certain specific value a, namely | h/δ | < a.
a is a number less than 1.
In the step (3), the actual defect dimension h in the flying process of the aircraft meets the requirement
h＝h0+h'
|h/δ|<a
Wherein h is0H 'is the defect scale to be processed initially, h' is the defect scale caused by thermal deformation, and is calculated by thermal deformation data of each section, | h/delta |<a is the constrained range of the defect scale, and δ is the thickness of the boundary layer at the position of the defect.
And performing flow field calculation on the aircraft by using an engineering method or a numerical simulation method, and extracting and processing a flow field calculation result to obtain the boundary layer thickness delta at the position of the defect.
The method for calculating the defect size h' caused by thermal deformation from the thermal deformation data of each section comprises the following steps:
and projecting the thermal deformation of the two sections at the position of the defect in the defect scale direction, wherein the difference of the projection values of the two thermal deformation is the defect scale h'.
The positive and negative values of h' should be defined in relation to h0The positive and negative definitions remain consistent.
In the step (1), the defects include steps or gaps caused by butt joint of the cabin sections, steps, gaps or recesses formed by mounting the antenna window, and bulges or recesses formed by mounting the sensor.
In the step (1), the theoretical analysis means is transition mode method, eNThe method or the LES/DNS method.
In the step (1), the ground test is a calm wind tunnel test.
Compared with the prior art, the invention has the beneficial effects that:
(1) the method disclosed by the invention is used for controlling the defect scale in a hypersonic aircraft flight test, and the defect scale is ensured to meet the constraint range, so that the influence of the defect scale on the transition of the aircraft surface is effectively reduced, the pneumatic heating of the aircraft surface is prevented from being abnormally increased due to the transition, and the working reliability of the aircraft thermal protection system is improved.
(2) The invention provides a strategy for controlling the defect scale by utilizing mutual offset of the thermal deformation and the initial defect scale, which can effectively reduce the actual defect scale of the surface of the aircraft in the flight process, thereby reducing the local thermal increment caused by the defect, reducing the possibility of local ablation, better keeping the appearance integrity of the aircraft and ensuring the aerodynamic performance and the control reliability of the aircraft.
Drawings
FIG. 1 is a schematic diagram of the steps performed in the present invention;
FIG. 2 is a schematic diagram of a typical cabin segment structure and a docking step in the embodiment, wherein the docking step is formed between the end head and the rear cabin;
FIG. 3 is a schematic diagram showing the dimensions of the docking step in the embodiment;
FIG. 4 is a schematic diagram illustrating the thermal deformation of the tip and the rear cabin during flight in the embodiment;
FIG. 5 is a graph showing the control effect of the method provided by the present invention on the size of the butt-joint step of the head and the rear cabin in the embodiment.
Detailed Description
The invention provides a surface defect scale control method capable of reducing the influence on flow transition, aiming at the problem that the scale of defects such as steps, gaps and the like on the surface of the existing hypersonic flight vehicle is difficult to control reasonably.
As shown in fig. 1, the method is implemented as follows:
first, a theoretical analysis method (transition mode method, e) is usedNThe LES/DNS method) or the ground test means (generally adopting a static wind tunnel test) to carry out flow transition research on the aircraft, and obtain the constraint of surface defect dimensions (steps, gaps and the like) which meet the requirement of transition of the boundary layer without influenceAnd (3) a range. The constraint range of the defect scale is characterized in that the ratio | h/delta | of the defect scale h to the boundary layer thickness delta of the position of the defect is smaller than a certain value a, namely | h/delta<a, wherein a is a number less than 1.
And then carrying out pneumatic heating, structural temperature field and deformation field combined simulation analysis on the sections with the defects of steps, gaps and the like to obtain thermal deformation data of each section in the flight process.
And the final actual defect scale is ensured to meet the constraint range by designing the defect scales such as steps and gaps to be initially processed and utilizing the strategy of counteracting the thermal deformation amount by the initially processed defect scale.
The actual defect dimension h in the flying process of the aircraft meets
h＝h0+h'
|h/δ|<a
Wherein h is0H 'is the defect scale to be processed initially, and h' is the defect scale caused by thermal deformation, and is calculated by thermal deformation data of each section. And performing flow field calculation on the aircraft by using an engineering method or a numerical simulation method, and extracting and processing a flow field calculation result to obtain the boundary layer thickness delta at the position of the defect.
Projecting the thermal deformation of two sections at the position of the defect in the direction of the defect scale, wherein the difference of the projection values of the two thermal deformation is the defect scale h ', and the positive and negative definitions of h ' and h ' should be matched with h0The positive and negative definitions remain consistent.
The aircraft surface defect scale control method provided by the invention utilizes a strategy of counteracting the thermal deformation and the initial defect scale, can reasonably and effectively control the aircraft surface defect scale, reduces the possibility of inducing surface transition, and ensures the reliable work of an aircraft thermal protection system.
Example (b):
the specific embodiment of the invention is illustrated by taking the control of the height of the docking step between two sections of an aircraft as an example. As shown in fig. 2, a butt step is formed between the two sections of the head and the rear cabin.
As shown in fig. 3, the step height to be processed is defined as h0Flying aircraftThe actual step height in the line process is h; because the structure of the end head is different from that of the rear cabin, the end head is solid, the material of the end head is different from that of the rear cabin, the difference of thermal response of the end head and the rear cabin can cause the difference of deformation at a butt joint position in the flying process, the difference of thermal deformation of two cabin sections can generate an extra step, the height of the extra step is defined as h', and the height of the step when the shell of the rear cabin is higher than the end head is defined as a positive value. The implementation steps of the butt joint step size control method provided by the invention are as follows:
1. using theoretical analysis means (e.g. transition mode method, e)NTransition prediction methods such as LES/DNS (Linear engineering System)/the like) or ground test (generally static wind tunnel test) means are used for developing flow transition research on the aircraft, a step size constraint requirement which does not influence the flow transition of the surface of the aircraft is obtained through analysis, and the requirement is represented by the condition that the ratio h/delta of the step height to the boundary layer thickness delta at the position of the step is smaller than a certain specific value<a, wherein a is a number less than 1;
2. performing calculation and analysis on the pneumatic heating of the aircraft to obtain the surface heat flow distribution of the aircraft, performing calculation and analysis on a structural temperature field and a structural deformation field by taking the surface heat flow distribution of the aircraft as input, extracting the thermal deformation of two cabin sections at the position of a butt joint step from a structural deformation calculation result, then projecting the deformation of the two cabin sections in the height direction of the butt joint step to obtain end deformation projection data d1The projection data of the deformation of the rear cabin shell is d2Then the extra step height h' ═ d2-d1；
3. Carrying out flow field calculation on the aircraft by using an engineering method or a numerical simulation method, and extracting and processing flow field calculation results to obtain the information of the boundary layer thickness delta at the position of the butt joint step;
4. designing the height h of the step to be processed according to the constraint requirement obtained in the step 1 and the strategy of offsetting the initial processing step from the additional step generated by the structural deformation0The specific calculation formula is as follows:
h＝h0+h′
(d1-d2)-aδ＜h0＜(d1-d2)+aδ
the step machining height h meeting the constraint requirement can be obtained according to the formula0A range of (d);
5. h is obtained according to step 40And (4) formulating the size processing requirement of the cabin section, and ensuring that the height of the initial butt joint step after assembly is within a design value range.
The effect of the embodiment is illustrated by fig. 4 and 5, fig. 4 is a schematic view of the thermal deformation of the head and the rear cabin during flight, and it can be seen from the figure that the step height caused by thermal deformation mismatch of different cabin sections is considerable.
Fig. 5 shows the control effect of the method provided by the present invention on the step size. As can be seen from fig. 5, the step resulting purely from the deformation is at time of flight t ═ t0And after +6s, the step height constraint is exceeded, and the initial step height and the deformation are offset through the initial step height with reasonable design, so that the final step height is always within the constraint range. The method is successfully implemented in a flight test, the effect is good, the step height is effectively controlled, and flight test data show that the surface flow transition of the aircraft is not influenced by the step height.
The aircraft surface defect scale control method provided by the invention is not only suitable for butt joint of the cabin sections with steps, gaps and the like, but also suitable for controlling steps, gaps and recesses formed by mounting antenna windows, bulges/recesses formed by mounting sensors and other types of surface defect scales.
The above-mentioned embodiments are merely illustrative of the present invention and should not be construed as limiting the present invention, and therefore, any embodiments similar to the concept of the present invention or other embodiments with similar structure but with similar concept are within the scope of the present invention.
The invention is not described in detail and is within the knowledge of a person skilled in the art.

Claims (10)

1. A control method for reducing the influence on flow transition on the surface defect scale of an aircraft is characterized by comprising the following steps:
(1) carrying out flow transition research on the aircraft by using a theoretical analysis means or a ground test means to obtain a constraint range of a surface defect scale which meets the requirement that the transition of the boundary layer is not influenced;
(2) performing pneumatic heating analysis on the aircraft to obtain the surface heat flow distribution of the aircraft, performing combined simulation analysis on a structural temperature field and a deformation field of the aircraft by taking the surface heat flow distribution of the aircraft as input, and extracting thermal deformation data of each section generating defects in the flight process from the structural deformation calculation result;
(3) and (3) designing the initial defect scale to be processed according to the constraint range and the thermal deformation data obtained in the steps (1) and (2) by utilizing a strategy of counteracting the thermal deformation by utilizing the initial defect scale, and ensuring that the actual defect scale in the flight process meets the constraint range.
2. The aircraft surface defect scale control method for reducing the impact on flow transition as claimed in claim 1, wherein: in the step (1), the constraint range of the defect scale is characterized in that the ratio | h/δ | of the defect scale h to the boundary layer thickness δ of the position where the defect is located is smaller than a certain specific value a, namely | h/δ | < a.
3. The aircraft surface defect scale control method for reducing the impact on flow transition as claimed in claim 2, wherein: a is a number less than 1.
4. The aircraft surface defect scale control method for reducing the impact on flow transition as claimed in claim 1, wherein: in the step (3), the actual defect dimension h in the flying process of the aircraft meets the requirement
h＝h0+h'
|h/δ|<a
Wherein h is0H 'is the scale of the defect to be processed initially, h' is the scale of the defect caused by thermal deformation, and the data of the thermal deformation amount of each sectionCalculated to obtain | h/delta | Y<a is the constrained range of the defect scale, and δ is the thickness of the boundary layer at the position of the defect.
5. The aircraft surface defect scale control method for reducing the impact on flow transition as claimed in claim 2 or 4, wherein: and performing flow field calculation on the aircraft by using an engineering method or a numerical simulation method, and extracting and processing a flow field calculation result to obtain the boundary layer thickness delta at the position of the defect.
6. The aircraft surface defect scale control method for reducing the impact on flow transition as claimed in claim 4, wherein: the method for calculating the defect size h' caused by thermal deformation from the thermal deformation data of each section comprises the following steps:
and projecting the thermal deformation of the two sections at the position of the defect in the defect scale direction, wherein the difference of the projection values of the two thermal deformation is the defect scale h'.
7. The aircraft surface defect scale control method for reducing the impact on flow transition as claimed in claim 6, wherein: the positive and negative values of h' should be defined in relation to h0The positive and negative definitions remain consistent.
8. The aircraft surface defect scale control method for reducing the impact on flow transition as claimed in claim 1, wherein: in the step (1), the defects include steps or gaps caused by butt joint of the cabin sections, steps, gaps or recesses formed by mounting the antenna window, and bulges or recesses formed by mounting the sensor.
9. The aircraft surface defect scale control method for reducing the impact on flow transition as claimed in claim 1, wherein: in the step (1), the theoretical analysis means is transition mode method, eNThe method or the LES/DNS method.
10. The aircraft surface defect scale control method for reducing the impact on flow transition as claimed in claim 1, wherein: in the step (1), the ground test is a calm wind tunnel test.
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Cited By (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN112304563A (en) * 2020-10-30 2021-02-02 中国空气动力研究与发展中心超高速空气动力研究所 Wind tunnel test method for researching influence of transition on aerodynamic characteristics of hypersonic aircraft
CN112613122A (en) * 2020-12-24 2021-04-06 中国航空工业集团公司西安飞机设计研究所 Design method for controlling top-level parameters of airplane through laminar flow

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CN101318553A (en) * 2008-05-28 2008-12-10 中国航天空气动力技术研究院 Wing flow control device
US20180105258A1 (en) * 2016-10-14 2018-04-19 U.S.A. as represented by the Administrator of NASA Method and System for Delaying Laminar-To-Turbulent Transition in High-Speed Boundary Layer Flow
US20180244370A1 (en) * 2017-02-18 2018-08-30 Jean-Eloi William Lombard Passive flow control mechanism for suppressing tollmien-schlichting waves, delaying transition to turbulence and reducing drag

Patent Citations (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN101318553A (en) * 2008-05-28 2008-12-10 中国航天空气动力技术研究院 Wing flow control device
US20180105258A1 (en) * 2016-10-14 2018-04-19 U.S.A. as represented by the Administrator of NASA Method and System for Delaying Laminar-To-Turbulent Transition in High-Speed Boundary Layer Flow
US20180244370A1 (en) * 2017-02-18 2018-08-30 Jean-Eloi William Lombard Passive flow control mechanism for suppressing tollmien-schlichting waves, delaying transition to turbulence and reducing drag

Cited By (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN112304563A (en) * 2020-10-30 2021-02-02 中国空气动力研究与发展中心超高速空气动力研究所 Wind tunnel test method for researching influence of transition on aerodynamic characteristics of hypersonic aircraft
CN112613122A (en) * 2020-12-24 2021-04-06 中国航空工业集团公司西安飞机设计研究所 Design method for controlling top-level parameters of airplane through laminar flow
CN112613122B (en) * 2020-12-24 2022-10-11 中国航空工业集团公司西安飞机设计研究所 Design method for controlling top-level parameters of airplane through laminar flow

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