CN113933033B - Ground test system and method for heat-proof skirt - Google Patents
Ground test system and method for heat-proof skirt Download PDFInfo
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- CN113933033B CN113933033B CN202110988288.8A CN202110988288A CN113933033B CN 113933033 B CN113933033 B CN 113933033B CN 202110988288 A CN202110988288 A CN 202110988288A CN 113933033 B CN113933033 B CN 113933033B
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- G—PHYSICS
- G01—MEASURING; TESTING
- G01M—TESTING STATIC OR DYNAMIC BALANCE OF MACHINES OR STRUCTURES; TESTING OF STRUCTURES OR APPARATUS, NOT OTHERWISE PROVIDED FOR
- G01M13/00—Testing of machine parts
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- G—PHYSICS
- G01—MEASURING; TESTING
- G01B—MEASURING LENGTH, THICKNESS OR SIMILAR LINEAR DIMENSIONS; MEASURING ANGLES; MEASURING AREAS; MEASURING IRREGULARITIES OF SURFACES OR CONTOURS
- G01B21/00—Measuring arrangements or details thereof, where the measuring technique is not covered by the other groups of this subclass, unspecified or not relevant
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- G—PHYSICS
- G01—MEASURING; TESTING
- G01B—MEASURING LENGTH, THICKNESS OR SIMILAR LINEAR DIMENSIONS; MEASURING ANGLES; MEASURING AREAS; MEASURING IRREGULARITIES OF SURFACES OR CONTOURS
- G01B21/00—Measuring arrangements or details thereof, where the measuring technique is not covered by the other groups of this subclass, unspecified or not relevant
- G01B21/02—Measuring arrangements or details thereof, where the measuring technique is not covered by the other groups of this subclass, unspecified or not relevant for measuring length, width, or thickness
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- G—PHYSICS
- G01—MEASURING; TESTING
- G01B—MEASURING LENGTH, THICKNESS OR SIMILAR LINEAR DIMENSIONS; MEASURING ANGLES; MEASURING AREAS; MEASURING IRREGULARITIES OF SURFACES OR CONTOURS
- G01B21/00—Measuring arrangements or details thereof, where the measuring technique is not covered by the other groups of this subclass, unspecified or not relevant
- G01B21/22—Measuring arrangements or details thereof, where the measuring technique is not covered by the other groups of this subclass, unspecified or not relevant for measuring angles or tapers; for testing the alignment of axes
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- G—PHYSICS
- G01—MEASURING; TESTING
- G01M—TESTING STATIC OR DYNAMIC BALANCE OF MACHINES OR STRUCTURES; TESTING OF STRUCTURES OR APPARATUS, NOT OTHERWISE PROVIDED FOR
- G01M15/00—Testing of engines
- G01M15/14—Testing gas-turbine engines or jet-propulsion engines
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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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- Engineering & Computer Science (AREA)
- Combustion & Propulsion (AREA)
- Testing Of Engines (AREA)
Abstract
The invention provides a heat protection skirt ground test system and a heat protection skirt ground test method. The invention solves the design problem that the fireproof skirt is simultaneously suitable for the combined swinging working condition of the engine and the body flap. The design of the engine overhanging plate component is innovatively provided, the distance between a nozzle connecting port and a heat-proof skirt is improved, and the risk of flame ablation entering is reduced. Can meet the requirements of control professions and also can meet the heat-proof function. The project achievement is suitable for various small spacecrafts, missile weapons and the like, and belongs to the technical field of light and small spaceflight.
Description
Technical Field
The invention relates to a ground test tool design of a heat-proof skirt and a heat-proof skirt test scheme. The heat-proof function of the tail end surface of the carrier can be met, the deflection angle requirements of the engine and the body flap can be met, and the heat-proof function belongs to the field of the flying back and forth vehicle.
Background
The sub-orbit reuse carrier adopts a new generation liquid oxygen kerosene engine main power system and is an important development direction of an aerospace transportation system. The heat-proof skirt is an important general assembly straight member on the aircraft, not only can meet the heat-proof and heat-proof functions of the tail end surface of the carrier, but also can meet the deflection angle requirements of the engine and the body flap.
The distance between the end face of the nozzle opening of the traditional carrier rocket type engine and the tail end face of the rear cabin body is about 1 meter, the bottom end face has no body flap control surface structure, the heat-proof skirt is connected with the gap between the root of the engine nozzle and the bottom end face of the rear cabin body, and the heat-proof function is realized under the working condition of adapting to the deflection of the nozzle in all directions. The risk of the heat-resistant skirt entering the flame area is small, and the heat-resistant skirt is only suitable for swinging of the engine spray pipe. The design regularity is strong, and the design method is more consistent.
Unlike the traditional carrier rocket state, the nozzle opening of the sub-orbit reuse aircraft engine is very close to the tail end surface of the rear cabin by about 115 mm, and the thermal environment condition is harsh. And the tail end frame bottom has body flap rudder surface structure, and the heat protection skirt needs to protect tail end frame and structures such as engine clearance, body flap journal stirrup, need adapt to engine swing and body flap joint swing simultaneously moreover, and the degree of difficulty is great, and the novelty is stronger.
The ground tool and the test scheme for establishing the heat-proof skirt are necessary preconditions for realizing the scheme design of the heat-proof skirt of the sub-orbit reusable aircraft.
Disclosure of Invention
The technical solution of the invention is as follows: the design method is suitable for the structural characteristics of the short distance between the spray pipe and the tail end surface, overcomes the severe thermal environment condition, establishes a ground test scheme of the heat-proof skirt, and realizes the scheme design of the sub-track reusable aircraft heat-proof skirt.
The technical scheme of the invention is as follows: the ground test tool of the heat protection skirt comprises a support platform, an engine spray pipe test simulation piece connecting section, an engine spray pipe simulation piece angle adjusting mechanism assembly, a body flap support lug simulation piece angle adjusting mechanism assembly, a rear cabin tail end face simulation piece and an engine overhanging plate assembly;
the support platform is formed by welding channel steel and is used as a main framework for supporting each test simulation piece and the connecting structure; the engine spray pipe test simulation piece is fixedly connected with the engine spray pipe test simulation piece connecting section through bolts, the engine spray pipe test simulation piece connecting section is fixedly connected with the support platform through the universal wheel mechanism, one end of the engine spray pipe test simulation piece connecting section is connected with the engine spray pipe simulation piece angle adjusting mechanism component, and the other end of the engine spray pipe test simulation piece connecting section is fixedly connected with the support platform; the engine spray pipe simulation piece angle adjusting mechanism component mechanism enables the engine spray pipe simulation piece to rotate 360 degrees around the fulcrum through the engine spray pipe test simulation piece connecting section; one end of the body flap support lug simulation piece angle adjusting mechanism component is connected with the body flap support lug simulation piece, the other end of the body flap support lug simulation piece angle adjusting mechanism component is fixedly connected with the support platform, and swing of the body flap support lug is realized through an adjusting mechanism; the rear cabin tail end surface simulation piece is welded on the bracket platform structure and is used for connecting and mounting a large-diameter port end of the heat-proof skirt product; the engine overhanging plate assembly is connected and installed on an interface of an engine spray pipe test simulation piece through bolts and is used for connecting and installing a small-diameter port end of a heat-proof skirt product.
The engine spray pipe test simulation piece has bidirectional swinging capability through the angle adjusting mechanism, realizes angle adjustment within an upper-lower 5-degree range, and adapts to 5 degrees and inner swinging angles in any direction.
The body flap lug simulation piece has up-and-down swinging capability through the angle adjusting mechanism, and an angle of 20 degrees of up-swinging and 30 degrees of down-swinging is realized.
The engine spray pipe adjusting mechanism assembly and the body flap lug simulator angle adjusting mechanism assembly are formed by connecting rods and threaded pull rods.
The rear end face simulation piece of the rear cabin is in non-concentric relation with the engine overhanging plate assembly, and the center positions of the front and rear parts are different by +28mm in the y direction under the full machine coordinate system.
The simulation piece of the tail end surface of the rear cabin has 34 through holes on a scale circle with the diameter of phi 1055mm, and each 10-degree phase has 1 through hole with the diameter of phi of 6.5.
After the engine spray pipe test simulation piece is installed and connected with the engine overhanging plate assembly, 33 through holes are formed in the phi 800mm indexing circle, and are unevenly distributed.
A ground test method of a heat-proof skirt comprises the following steps:
step one, adjusting an engine spray pipe simulation piece to be at a 0-degree position by utilizing an engine spray pipe simulation piece angle adjusting mechanism assembly, and installing a fireproof skirt product on an engine spray pipe test simulation piece product and a body flap support lug simulation piece through an M6 bolt after adjusting the body flap support lug simulation piece to be at a horizontal 0-degree position by utilizing a body flap support lug simulation piece angle adjusting mechanism assembly;
step two, according to the special control requirement of attitude control, the test fixture adjusts the rotation angles of an engine spray pipe simulation piece and a body flap support lug simulation piece through simulating the flight working condition, and a test simulation plan is formulated, wherein the test simulation plan comprises determining the dimension specification of a fireproof skirt lower piece and deflection angle interference inspection; through experimental simulation, the tool adjusts working conditions to truly simulate the flight state, and verification of the design scheme of the heat protection skirt is realized.
The specific method for determining the dimension specification of the fireproof skirt lower part comprises the following steps: after the body flap is fixed at a certain angle (0 degree, 30 degrees and minus 20 degrees), the engine spray pipe simulation piece swings at 5 degrees in 8 directions of pitching, yawing and diagonal, and whether the bus length of the fireproof skirt lower piece is suitable for the swinging working condition is checked.
The specific method for deflection angle interference inspection comprises the following steps:
static interference checking: installing an upper part and a lower part of the fireproof skirt, and checking the adaptation condition of the fireproof skirt in a swinging state; the engine nozzle simulation piece is fixed on the flap at a certain angle (0 degree, 5 degree, 10 degree and 20 degree), and the pitching and yaw of the engine nozzle simulation piece are respectively deflected by 5 degrees in 4 directions; measuring the distance between the inner layer and the outer layer near the flap lugs of the lower part body of the fireproof skirt;
dynamic interferometry: installing an upper part and a lower part of the fireproof skirt, fixing an engine spray pipe at a certain angle, dynamically swinging a body flap simulation part [ -20 degrees, +30 degrees ], and checking whether the body flap can dynamically swing without interference;
dynamic interferometry: and installing an upper part and a lower part of the fireproof skirt, fixing the flap lugs at a certain angle, manually simulating the rounding process of the engine, and checking whether the vicinity of the flap lugs is in friction interference with the fireproof skirt.
The invention designs a novel heat-proof skirt ground test scheme, and the whole-course flight working condition of a carrier is effectively simulated through a ground engineering design, so that the novel design of the fire-proof skirt final assembly straight member scheme is completed. The heat-proof function of the tail end surface of the carrier can be met, and the deflection angle requirements of the engine and the body flap can be met. Compared with the prior art, the invention has the following beneficial effects:
(1) The heat-proof skirt ground test scheme provided by the invention can realize the relative position relation simulation of the engine spray pipe simulation piece, the rear cabin tail end surface simulation piece and the body flap support lug simulation piece, and effectively avoids the risks that the product does not meet the actual deflection working condition after three-dimensional design and two-dimensional blanking through a ground test.
(2) According to the ground test scheme of the heat protection skirt, through the ground test mechanism tool and the angle detector, accurate control of the swing angle of the engine spray pipe and the body flap is achieved, and the real flight swing working condition is simulated more accurately.
(3) According to the ground test scheme of the heat protection skirt, the design of the engine overhanging plate assembly is innovatively provided, the distance between the nozzle connecting opening of the engine and the heat protection skirt is greatly improved, and the risk of entering a flame area is reduced.
Drawings
FIG. 1 is a schematic diagram of a heat shield skirt ground test fixture of the present invention.
Detailed Description
As shown in fig. 1, the ground test fixture of the heat protection skirt comprises a bracket platform 1, an engine spray pipe test simulation piece 2, an engine spray pipe test simulation piece connecting section 3, an engine spray pipe simulation piece angle adjusting mechanism assembly 4, a body flap support lug simulation piece 5, a body flap support lug simulation piece angle adjusting mechanism assembly 6, a rear cabin tail end face simulation piece 7 and an engine overhanging plate assembly 8;
the support platform 1 is formed by welding channel steel and is used as a main framework for supporting each test simulation piece and a connecting structure; the engine spray pipe test simulation piece 2 is fixedly connected with the engine spray pipe test simulation piece connecting section 3 through bolts, the engine spray pipe test simulation piece connecting section 3 is fixedly connected with the support platform 1 through a universal wheel mechanism, one end of the engine spray pipe test simulation piece connecting section 3 is connected with the engine spray pipe simulation piece angle adjusting mechanism assembly 4, and the other end of the engine spray pipe test simulation piece connecting section is fixedly connected with the support platform 1; the engine spray pipe simulation piece angle adjusting mechanism component 4 is used for enabling the engine spray pipe simulation piece to rotate 360 degrees around the fulcrum through the engine spray pipe test simulation piece connecting section 3; one end of a body flap support lug simulation piece angle adjusting mechanism component 6 is connected with the body flap support lug simulation piece 5, the other end of the body flap support lug simulation piece angle adjusting mechanism component is fixedly connected with the support platform 1, and swing of the body flap support lug is realized through an adjusting mechanism 6; the rear cabin tail end face simulation piece 7 is welded on the structure of the bracket platform 1 and is used for connecting and mounting a large-diameter port end of the heat-proof skirt product; the engine overhanging plate assembly 8 is connected and installed on the interface of the engine spray pipe test simulation piece 2 through bolts and is used for connecting and installing the small-diameter port end of the heat-proof skirt product.
The engine spray pipe test simulation piece 2 has bidirectional swinging capability through an angle adjusting mechanism, realizes angle adjustment within an upper-lower 5-degree range, and adapts to 5 degrees and inner swinging angles in any direction.
The body flap lug simulation piece 5 has up-and-down swinging capability through the angle adjusting mechanism, and an angle of 20 degrees of up-swinging and 30 degrees of down-swinging is realized.
The engine nozzle adjusting mechanism assembly 4 and the body flap lug simulator angle adjusting mechanism assembly 6 are formed by connecting rods and threaded pull rods.
The rear cabin tail end face simulation piece 7 and the engine overhanging plate assembly 8 are in a non-concentric relation, and the center positions of the front cabin tail end face simulation piece and the engine overhanging plate assembly are different by +28mm in the y direction under a full machine coordinate system.
The number of through holes of the rear end face simulation piece 7 on the scale circle with the diameter of phi 1055mm is 34, and each 10-degree phase is provided with 1 through hole with the diameter of phi of 6.5.
After the engine spray pipe test simulation piece 2 is installed and connected with the engine overhanging board assembly 8, 33 through holes are distributed unevenly on the index circle with the diameter of phi 800 mm.
Through the design of engine overhanging board assembly 8, the heat-proof skirt and the engine spray pipe interface are changed, and the outside of the engine spray nozzle extends to the outer diameter of the overhanging board along the radial direction, so that the distance between the engine spray pipe connection port and the fire-proof skirt is improved, and the risk of entering a flame area is reduced.
The invention also relates to a ground test method of the heat-proof skirt, which comprises the following steps:
firstly, adjusting an engine spray pipe simulation piece 2 to be at a 0-degree position by utilizing an engine spray pipe simulation piece angle adjusting mechanism assembly 4, and after adjusting a body flap support lug simulation piece 5 to be at a horizontal 0-degree position by utilizing a body flap support lug simulation piece angle adjusting mechanism assembly 6, installing a fireproof skirt product on an engine spray pipe test simulation piece product 2 and the body flap support lug simulation piece 5 through an M6 bolt;
step two, according to the attitude control professional control requirement, the test tool adjusts the rotation angles of the engine spray pipe simulation piece 2 and the body flap support lug simulation piece 5 by simulating the flight working condition, and the following test plan is formulated:
A. determining the dimension specification of the fireproof skirt lower part: after the body flap is fixed at a certain angle (0 degree, 30 degrees and minus 20 degrees), the engine spray pipe simulation piece swings at 5 degrees in 8 directions of pitching, yawing and diagonal, and whether the bus length of the fireproof skirt lower piece is suitable for the swinging working condition is checked;
B. performing deflection angle interference check:
static interference checking: and installing an upper part and a lower part of the fireproof skirt, and checking the adaptation condition of the fireproof skirt in the swinging state. The engine jet pipe simulation piece of the fixed body flap has a certain angle (0 degree, 5 degree, 10 degree and 20 degree), and the pitching direction and the yaw direction of the engine jet pipe simulation piece are respectively 5 degrees. And measuring the distance between the inner layer and the outer layer near the flap lugs of the lower part body of the fireproof skirt.
Dynamic interferometry: the upper part and the lower part of the fireproof skirt are arranged, the engine spray pipe is fixed at a certain angle, and the dynamic swing body flap simulation part is [ -20 degrees, +30 degrees ], so as to check whether the body flap can dynamically swing without interference.
Dynamic interferometry: and installing an upper part and a lower part of the fireproof skirt, fixing the flap lugs at a certain angle, manually simulating the rounding process of the engine, and checking whether the vicinity of the flap lugs is in friction interference with the fireproof skirt.
Through the simulation of the two large series of tests, the tool adjusting working condition truly simulates the flight state, and the verification of the design scheme of the heat protection skirt is realized.
Although the present invention has been described with respect to the preferred embodiments, it is not intended to be limited thereto, and any person skilled in the art can make any possible variations and modifications to the technical solution of the present invention by using the technical matters disclosed above without departing from the spirit and scope of the present invention, so any simple modifications, equivalent variations and modifications to the above embodiments according to the technical matters of the present invention fall within the scope of the technical solution of the present invention.
Claims (10)
1. The utility model provides a ground test frock of heat protection skirt which characterized in that: the ground test tool comprises a support platform (1), an engine spray pipe test simulation piece (2), an engine spray pipe test simulation piece connecting section (3), an engine spray pipe simulation piece angle adjusting mechanism assembly (4), a body flap lug simulation piece (5), a body flap lug simulation piece angle adjusting mechanism assembly (6), a rear cabin tail end face simulation piece (7) and an engine overhanging plate assembly (8);
the support platform (1) is formed by welding channel steel and is used as a main framework for supporting each test simulation piece and the connecting structure; the engine spray pipe test simulation piece (2) is fixedly connected with the engine spray pipe test simulation piece connecting section (3) through bolts, the engine spray pipe test simulation piece connecting section (3) is fixedly connected with the support platform (1) through a universal wheel mechanism, one end of the engine spray pipe test simulation piece connecting section (3) is connected with the engine spray pipe simulation piece angle adjusting mechanism assembly (4), and the other end of the engine spray pipe test simulation piece connecting section is fixedly connected with the support platform (1); an engine spray pipe simulation piece angle adjusting mechanism assembly (4) enables the engine spray pipe simulation piece to rotate 360 degrees around a fulcrum through an engine spray pipe test simulation piece connecting section (3); one end of a body flap support lug simulation piece angle adjusting mechanism assembly (6) is connected with a body flap support lug simulation piece (5), the other end of the body flap support lug simulation piece angle adjusting mechanism assembly is fixedly connected with the support platform (1), and swing of the body flap support lug is realized through an adjusting mechanism (6); the rear cabin tail end face simulation piece (7) is welded on the structure of the bracket platform (1) and is used for connecting and installing a large-diameter port end of the heat-resistant skirt product; the engine overhanging plate assembly (8) is connected and installed on the interface of the engine spray pipe test simulation piece (2) through bolts and is used for connecting and installing the small-diameter port end of the heat-proof skirt product.
2. The ground test fixture of a heat shield skirt according to claim 1, wherein: the engine spray pipe test simulation piece (2) has bidirectional swinging capability through an angle adjusting mechanism, realizes angle adjustment within an upper-lower 5-degree range, and adapts to 5 degrees and inner swinging angles in any direction.
3. The ground test fixture of a heat shield skirt according to claim 1, wherein: the body flap lug simulation piece (5) has up-and-down swinging capability through the angle adjusting mechanism, and an angle of 20 degrees of up-swinging and 30 degrees of down-swinging is realized.
4. The ground test fixture of a heat shield skirt according to claim 1, wherein: the engine spray pipe adjusting mechanism assembly (4) and the body flap lug simulation piece angle adjusting mechanism assembly (6) are formed by connecting rods and threaded pull rods.
5. The ground test fixture of a heat shield skirt according to claim 1, wherein: the rear cabin tail end face simulation piece (7) is in non-concentric relation with the engine overhanging plate assembly (8), and the center positions of the front cabin tail end face simulation piece and the engine overhanging plate assembly are different by +28mm in the y direction under a full-machine coordinate system.
6. The ground test fixture of a heat shield skirt according to claim 1, wherein: the simulation piece (7) of the tail end surface of the rear cabin has 34 through holes on a scale circle with the diameter of phi 1055mm, and each 10-degree phase has 1 through hole with the diameter of phi 6.5.
7. The ground test fixture of a heat shield skirt according to claim 1, wherein: the number of through holes on the index circle with the diameter of phi 800mm is 33 after the engine spray pipe test simulation piece (2) is installed and connected with the engine overhanging plate assembly (8), and the through holes are unevenly distributed.
8. A method for performing a heat shield skirt floor test using the tooling of claim 1, comprising the steps of:
step one, an engine nozzle simulator (2) is adjusted to be at a 0-degree position by utilizing an engine nozzle simulator angle adjusting mechanism assembly (4), and after a body flap lug simulator (5) is adjusted to be at a horizontal 0-degree position by utilizing a body flap lug simulator angle adjusting mechanism assembly (6), a fireproof skirt product is installed on an engine nozzle test simulator product (2) and the body flap lug simulator (5) through M6 bolts;
step two, according to the special control requirement of attitude control, the test fixture adjusts the rotation angles of the engine spray pipe simulation piece (2) and the body flap support lug simulation piece (5) through simulating the flight working condition, and a test simulation plan is formulated, wherein the test simulation plan comprises the steps of determining the dimension specification of the fireproof skirt lower piece and performing deflection angle interference inspection; through experimental simulation, the tool adjusts working conditions to truly simulate the flight state, and verification of the design scheme of the heat protection skirt is realized.
9. The method for testing the ground of the heat protection skirt according to claim 8, wherein the specific method for determining the dimension specification of the lower part of the heat protection skirt is as follows: and after the body flap is fixed at a certain angle and the engine spray pipe simulation piece swings at 5 degrees in 8 directions of pitching, yawing and diagonal, whether the bus length of the fireproof skirt lower piece is suitable for the swinging working condition is checked.
10. The method for testing the ground of the heat protection skirt according to claim 8, wherein the specific method for checking the deflection angle interference is as follows:
static interference checking: installing an upper part and a lower part of the fireproof skirt, and checking the adaptation condition of the fireproof skirt in a swinging state; the engine spray pipe simulation piece with a fixed body flap at a certain angle swings at 5 degrees in the pitch direction and the yaw direction; measuring the distance between the inner layer and the outer layer near the flap lugs of the lower part body of the fireproof skirt;
dynamic interferometry: installing an upper part and a lower part of the fireproof skirt, fixing an engine spray pipe at a certain angle, dynamically swinging a body flap simulation part [ -20 degrees, +30 degrees ], and checking whether the body flap can dynamically swing without interference;
dynamic interferometry: and installing an upper part and a lower part of the fireproof skirt, fixing the flap lugs at a certain angle, manually simulating the rounding process of the engine, and checking whether the vicinity of the flap lugs is in friction interference with the fireproof skirt.
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| CN112505092A (en) * | 2020-10-27 | 2021-03-16 | 中国运载火箭技术研究院 | Heat-proof skirt gas flow test device |
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| CN112505092A (en) * | 2020-10-27 | 2021-03-16 | 中国运载火箭技术研究院 | Heat-proof skirt gas flow test device |
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| Title |
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| 硅橡胶涂覆织物的阻燃和烧蚀性能;毛科铸;罗丽娟;梁馨;方洲;唐一壬;;宇航材料工艺(05);全文 * |
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