CN116215874A - Heating device for thermal model test of aircraft - Google Patents
Heating device for thermal model test of aircraft Download PDFInfo
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- CN116215874A CN116215874A CN202310177980.1A CN202310177980A CN116215874A CN 116215874 A CN116215874 A CN 116215874A CN 202310177980 A CN202310177980 A CN 202310177980A CN 116215874 A CN116215874 A CN 116215874A
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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
- B64F5/60—Testing or inspecting aircraft components or systems
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- Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
- Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
- Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
- Y02T90/00—Enabling technologies or technologies with a potential or indirect contribution to GHG emissions mitigation
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- Aviation & Aerospace Engineering (AREA)
- Investigating Or Analyzing Materials Using Thermal Means (AREA)
Abstract
The invention relates to a heating device for a thermal model test of an aircraft, which comprises a tested aircraft and a heating device, wherein the tested aircraft is arranged on the heating device, the heating device comprises a movable base, a fixed bracket, a lamp tube fixing plate, a quartz lamp tube and a regulating and controlling device, and the fixed bracket is arranged on the movable base; the lamp tube fixing plate is arranged on the fixing bracket, and the inner side dimension of the lamp tube fixing plate is similar to the cross section dimension of the tested aircraft and is correspondingly arranged according to the shape of the tested aircraft so as to adapt to the aircraft with different shapes; the quartz lamp tube is arranged on the lamp tube fixing plate; the regulating device is arranged on the fixed bracket and used for regulating the temperature of the quartz lamp tube. The invention has the beneficial effects that: 1. the thermal environment can be applied to the tested aircrafts with different shapes in the mode experiment; 2. the influence of pneumatic heating in flight can be effectively simulated, and the thermal model characteristic of the aircraft can be obtained; 3. reasonable design, low maintenance cost and extremely high universality.
Description
Technical Field
The invention relates to the technical field of aircraft tests, in particular to a heating device for an aircraft thermal model test.
Background
With the continuous progress of technology, various technologies of aircrafts are also continuously improved. The hypersonic aircraft has the characteristics of high flying speed, high flying height and the like, and also becomes a high point for future strategic attack and defensive weapon development. For hypersonic aircraft, the aerodynamic heating environment facing the aircraft is more and more severe with the increasing flying speed. The aerodynamic heating effect can generate a transient thermal environment characterized by high temperature and large temperature gradient on the surface and the inside of the aircraft, and the transient thermal environment can have a significant influence on the modal characteristics of the aircraft, so that the flutter characteristics and the control characteristics of the aircraft are greatly influenced, and safety accidents are caused. Therefore, studying the modal characteristics of hypersonic aircraft structures in aerodynamic thermal environments is very important for the safety and reliability design of the aircraft.
A great deal of research on the thermal model characteristics of the airfoil structures at home and abroad is carried out, and the research on the thermal model characteristics of the whole aircraft is less. The conventional heating device for the thermal model test generally adopts a flat quartz lamp heating array, is mainly applied to airfoil structures, and is not suitable for aircrafts with pneumatic heating all around.
Disclosure of Invention
The embodiment of the invention provides a heating device for a thermal model test of an aircraft, which can solve the problems in the related art: the research on the airfoil surface type at home and abroad is less, and a flat quartz lamp heating array is generally adopted in a thermal mode test heating device, so that the device is not suitable for the problem that the periphery is subjected to pneumatic heating.
In one aspect, the embodiment of the invention provides a heating device for a thermal model test of an aircraft,
the device comprises a tested aircraft and a heating device, wherein the tested aircraft is arranged on the heating device, the heating device comprises a movable base, a fixed bracket, a lamp tube fixing plate, a quartz lamp tube and a regulating and controlling device, and the fixed bracket is arranged on the movable base; the lamp tube fixing plate is arranged on the fixing bracket, and the inner side dimension of the lamp tube fixing plate is similar to the cross section dimension of the tested aircraft and is used for being correspondingly arranged according to the shape of the tested aircraft so as to adapt to the aircraft with different shapes; the quartz lamp tube is arranged on the lamp tube fixing plate; the regulating and controlling device is arranged on the fixed support, the fixed support is used for regulating the temperature of the quartz lamp tube, and the heating devices are symmetrically arranged on two sides of the tested aircraft in pairs, so that the temperature of the single heating device can be regulated and controlled according to actual requirements, and further different heating devices can be heated according to different temperature conditions, so that the heated state of the tested aircraft in the flight can be simulated more truly.
In some embodiments, the heating device is provided with at least one group for heating the tested aircraft of different lengths.
In some embodiments, the heating devices are symmetrically arranged on two sides of the tested aircraft.
In some embodiments, a gantry is included, the bottom of which is fixedly attached to the foundation.
In some embodiments, a resilient suspension is attached to the top of the gantry.
In some embodiments, the elastic suspension device is used to suspend the aircraft under test.
In some embodiments, two ends of the quartz lamp tube are movably connected with the lamp tube fixing plate, so as to facilitate the installation of the elastic suspension device.
In some embodiments, the heating device comprises a foundation, and the heating device is arranged on the foundation through the movable base.
In some embodiments, a roller is connected below the movable base.
In some embodiments, the rollers are universal wheels and are provided with locking means for facilitating movement and securement of the heating means on the foundation.
The technical scheme provided by the invention has the beneficial effects that: 1. the thermal environment can be applied to the tested aircrafts with different shapes in the mode experiment; 2. the influence of pneumatic heating in flight can be effectively simulated, and the thermal model characteristic of the aircraft can be obtained; 3. reasonable design, low maintenance cost and extremely high universality.
Drawings
In order to more clearly illustrate the technical solutions of the embodiments of the present invention, the drawings required for the description of the embodiments will be briefly described below, and it is apparent that the drawings in the following description are only some embodiments of the present invention, and other drawings may be obtained according to these drawings without inventive effort for a person skilled in the art.
FIG. 1 is a schematic view of a heating device in a thermal model test heating device for an aircraft according to one embodiment of the present invention;
FIG. 2 is a second schematic view of a heating device in a thermal model test heating device for an aircraft according to the present invention;
FIG. 3 is a front view of an aircraft thermal modeling test heating apparatus of the present invention;
fig. 4 is a side view of an aircraft thermal model test heating apparatus according to the present invention.
In the figure: 1. a tested aircraft; 2. a heating device; 3. a movable base; 4. a fixed bracket; 5. a lamp tube fixing plate; 6. a quartz lamp tube; 7. a regulating device; 8. a portal frame; 9. an elastic suspension device; 10. a foundation; 11. and a roller.
Detailed Description
For the purpose of making the objects, technical solutions and advantages of the embodiments of the present invention more apparent, the technical solutions of the embodiments of the present invention will be clearly and completely described below with reference to the accompanying drawings in the embodiments of the present invention, and it is apparent that the described embodiments are some embodiments of the present invention, but not all embodiments of the present invention. All other embodiments, which can be made by those skilled in the art based on the embodiments of the invention without making any inventive effort, are intended to be within the scope of the invention.
Referring to fig. 1 to 2, the embodiment of the invention provides a heating device for a thermal model test of an aircraft, which comprises a tested aircraft 1 and a heating device 2, wherein the tested aircraft 1 is arranged on the heating device 2, the heating device 2 comprises a movable base 3,
the fixed bracket 4 is arranged on the movable base 3;
the lamp tube fixing plate 5 is arranged on the fixing bracket 4, and the inner side dimension of the lamp tube fixing plate 5 is similar to the cross section dimension of the tested aircraft 1 and is correspondingly arranged according to the shape of the tested aircraft 1 so as to adapt to the aircraft with different shapes;
the quartz lamp tube 6 is arranged on the lamp tube fixing plate 5;
the regulating and controlling device 7 is arranged on the fixed support 4 and is used for regulating the temperature of the quartz lamp tube 6, and as the heating devices 2 are symmetrically arranged on two sides of the tested aircraft 1 in pairs, the single heating device 2 can regulate and control the temperature according to actual requirements, so that different heating devices 2 can heat according to different temperature conditions, and the heated state of the tested aircraft 1 in flight can be simulated more truly.
In this embodiment, the size of the inner side of the lamp tube fixing plate 5 is the same as the cross-sectional size of the tested aircraft 1, and the cross-sectional size of the aircraft may be designed into different shapes such as round, square or irregular, so the size of the inner side of the lamp tube fixing plate 5 is the same as the cross-sectional size of the tested aircraft 1 according to the requirement. When the cross section of the actual tested aircraft 1 is circular, the inner side of the lamp tube fixing plate 5 is set to be circular, and at the moment, the tested aircraft 1 which is preferably circular can be heated; when the cross section of the actual tested aircraft 1 is square, the tested aircraft 1 which is square can be heated better; when the cross-sectional dimensions of the actual aircraft under test 1 are profiled, it is better to heat the aircraft under test 1 that is profiled.
Wherein, owing to including regulation and control device 7, regulation and control device 7 is located on fixed bolster 4 for the temperature of regulation quartz fluorescent tube 6. Because the heating devices 2 are symmetrically arranged at two sides of the tested aircraft 1 in pairs, the single heating device 2 can regulate and control the temperature according to actual requirements, and further, different heating devices 2 can heat according to different temperature conditions, so that the heated state of the tested aircraft 1 in flight can be simulated more truly.
Optionally, the heating device 2 is provided with at least one group for heating the tested aircraft 1 with different lengths.
In this embodiment, when the length of the tested aircraft 1 can be simulated by only using one set of heating devices 2, a set of heating devices are arranged on two sides of the tested aircraft 1, and the tested aircraft 1 is heated and simulated; when the length of the tested aircraft 1 is increased, the heating devices 2 can be increased or decreased at the two sides of the tested aircraft 1 according to actual requirements.
Optionally, the heating devices 2 are symmetrically arranged on two sides of the tested aircraft 1 in pairs.
In this embodiment, the heating devices 2 are symmetrically disposed on two sides of the tested aircraft 1. Because the heating device 2 is composed of two modules in the left-right direction, the heating surface can be conveniently covered on the surface of the tested aircraft 1 according to the needs through the butt joint of the left module and the right module.
Referring to fig. 3 to 4, optionally, a gantry 8 is included, and the bottom of the gantry 8 is fixedly connected to the foundation 10.
Optionally, an elastic suspension device 9 is connected to the top of the portal frame 8.
Optionally, the elastic suspension device 9 is used for suspending the tested aircraft 1.
Optionally, two ends of the quartz lamp tube 6 are movably connected with the lamp tube fixing plate 5, so as to facilitate the installation of the elastic suspension device 9.
In this embodiment, two ends of the quartz lamp tube 6 are movably connected with the lamp tube fixing plate 5, so as to facilitate the installation of the elastic suspension device 9. When the vibration excitation rod, the suspension rope, the sensor cable and the like are installed, the two ends of the quartz lamp tube 6 are movably connected with the lamp tube fixing plate 5, so that the positions are adjustable, and when the vibration excitation rod, the suspension rope, the sensor cable and the like are required to be installed, the two ends of the quartz lamp tube 6 can be adjusted, so that the installation of the elastic suspension device 9 and the installation of the vibration excitation rod, the sensor cable and the like can be facilitated.
Optionally, the heating device 2 comprises a foundation 10, and the heating device is arranged on the foundation 10 through the movable base 3.
As shown in fig. 1 to 4, optionally, a roller 11 is connected below the movable base 3.
Optionally, the roller 11 is a universal wheel, and is provided with locking means for facilitating the movement and fixing of the heating device 2 on the foundation 10.
In this embodiment, a roller 11 is connected below the movable base 3, the roller 11 is a universal wheel, and a locking device is provided for facilitating the movement and fixing of the heating device 2 on the foundation 10. When the heating device 2 needs to be moved to the position of the tested aircraft 1, the locking device is only required to be opened, the heating device 2 is moved to the position of the tested aircraft 1, and then the locking device is closed, so that the heating device 2 can be conveniently moved and stopped on the foundation 10.
The operation mode of the invention is as follows:
1. mounting the portal frame 8 on the foundation 10;
2. two elastic suspension devices 9 are arranged on the portal frame 8;
3. the tested aircraft 1 is kept horizontally suspended by an elastic suspension device 9;
4. the roller 11 is arranged below the movable base 3;
5. the fixed bracket 4 is arranged on the movable base 3;
6. mounting the lamp tube fixing plate 5 on the fixing bracket 4;
7. mounting a quartz lamp tube 6 on the lamp tube fixing plate 5;
8. placing the assembled at least one set of heating devices 2 on the foundation 10;
9. the heating device 2 is moved to the left side and the right side of the tested aircraft 1 to be assembled into an integral heating device;
10. electrifying the quartz lamp tubes 6 of each group of heating devices 2, and adjusting the adjusting and controlling device 7 according to the requirements to adjust and control the temperature of the quartz lamp tubes 6;
11. the heating of the aircraft 1 under test is completed.
The invention has the beneficial effects that:
1. the thermal environment can be applied to the tested aircrafts with different shapes in the mode experiment;
2. the influence of pneumatic heating in flight can be effectively simulated, and the thermal model characteristic of the aircraft can be obtained;
3. reasonable design, low maintenance cost and extremely high universality.
In the description of the present invention, it should be noted that the azimuth or positional relationship indicated by the terms "upper", "lower", etc. are based on the azimuth or positional relationship shown in the drawings, and are merely for convenience of describing the present invention and simplifying the description, and are not indicative or implying that the apparatus or element in question must have a specific azimuth, be constructed and operated in a specific azimuth, and thus should not be construed as limiting the present invention. Unless specifically stated or limited otherwise, the terms "disposed," "connected," and "connected" are to be construed broadly, and may be, for example, fixedly connected, detachably connected, or integrally connected; can be mechanically or electrically connected; can be directly connected or indirectly connected through an intermediate medium, and can be communication between two elements. The specific meaning of the above terms in the present invention can be understood by those of ordinary skill in the art according to the specific circumstances.
It should be noted that in this application, relational terms such as "first" and "second" and the like are used solely to distinguish one entity or action from another entity or action without necessarily requiring or implying any actual such relationship or order between such entities or actions. Moreover, the terms "comprises," "comprising," or any other variation thereof, are intended to cover a non-exclusive inclusion, such that a process, method, article, or apparatus that comprises a list of elements does not include only those elements but may include other elements not expressly listed or inherent to such process, method, article, or apparatus.
The foregoing is only a specific embodiment of the invention to enable those skilled in the art to understand or practice the invention. Various modifications to these embodiments will be readily apparent to those skilled in the art, and the generic principles defined herein may be applied to other embodiments without departing from the spirit or scope of the invention. Thus, the present invention is not intended to be limited to the embodiments shown herein but is to be accorded the widest scope consistent with the principles and novel features disclosed herein.
Claims (10)
1. The heating device for the thermal model test of the aircraft is characterized by comprising a tested aircraft (1) and a heating device (2), wherein the tested aircraft (1) is arranged on the heating device (2), the heating device (2) comprises a movable base (3),
the fixed bracket (4) is arranged on the movable base (3);
the lamp tube fixing plate (5) is arranged on the fixing bracket (4), and the inner side dimension of the lamp tube fixing plate (5) is similar to the cross section dimension of the tested aircraft (1) and is correspondingly arranged according to the shape of the tested aircraft (1) so as to adapt to the aircrafts with different shapes;
the quartz lamp tube (6) is arranged on the lamp tube fixing plate (5);
the regulation and control device (7) is arranged on the fixed support (4) and is used for adjusting the temperature of the quartz lamp tube (6), as the heating devices (2) are symmetrically arranged on two sides of the tested aircraft (1) in pairs, the single heating device (2) can regulate and control the temperature according to actual requirements, and then different heating devices (2) can be used for heating according to different temperature conditions, so that the heated state of the tested aircraft (1) in flight can be simulated more truly.
2. A thermal model test heating device for aircraft according to claim 1, characterized in that the heating device (2) is provided with at least one group for heating the aircraft under test (1) of different lengths.
3. The heating device for thermal model test of aircraft according to claim 1, wherein the heating devices (2) are symmetrically arranged on both sides of the aircraft (1) to be tested.
4. A thermal model test heating device for an aircraft according to claim 1, comprising a portal frame (8), the bottom of the portal frame (8) being fixedly connected to the foundation (10).
5. A thermal model test heating device for an aircraft according to claim 4, characterized in that the top of the portal frame (8) is connected with an elastic suspension device (9).
6. A thermal model test heating device for an aircraft according to claim 5, characterized in that the elastic suspension means (9) are used for suspending the aircraft under test (1).
7. A thermal model test heating device for an aircraft according to claim 6, characterized in that both ends of the quartz lamp tube (6) are movably connected with the lamp tube fixing plate (5) for facilitating the installation of the elastic suspension device (9).
8. A thermal model test heating device for an aircraft according to claim 1, characterized in that it comprises a foundation (10), said heating device (2) being provided on said foundation (10) by means of said mobile base (3).
9. A thermal model test heating device for an aircraft according to claim 1, characterized in that rollers (11) are connected below the movable base (3).
10. A thermal model test heating device for an aircraft according to claim 9, characterized in that the rollers (11) are universal wheels and are provided with locking means for facilitating the movement and fixing of the heating device (2) on the foundation (10).
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202310177980.1A CN116215874A (en) | 2023-02-28 | 2023-02-28 | Heating device for thermal model test of aircraft |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202310177980.1A CN116215874A (en) | 2023-02-28 | 2023-02-28 | Heating device for thermal model test of aircraft |
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| Publication Number | Publication Date |
|---|---|
| CN116215874A true CN116215874A (en) | 2023-06-06 |
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| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202310177980.1A Pending CN116215874A (en) | 2023-02-28 | 2023-02-28 | Heating device for thermal model test of aircraft |
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Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN117963157A (en) * | 2024-03-28 | 2024-05-03 | 南京工业大学 | Thermal test method and system for multi-temperature-zone structure of full-size hypersonic aircraft |
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2023
- 2023-02-28 CN CN202310177980.1A patent/CN116215874A/en active Pending
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN117963157A (en) * | 2024-03-28 | 2024-05-03 | 南京工业大学 | Thermal test method and system for multi-temperature-zone structure of full-size hypersonic aircraft |
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