CN112485012A - Solid rocket engine experiment table and stress testing method - Google Patents

Solid rocket engine experiment table and stress testing method Download PDF

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Publication number
CN112485012A
CN112485012A CN202011268544.8A CN202011268544A CN112485012A CN 112485012 A CN112485012 A CN 112485012A CN 202011268544 A CN202011268544 A CN 202011268544A CN 112485012 A CN112485012 A CN 112485012A
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CN
China
Prior art keywords
tail nozzle
end tail
support
bolt
rocket engine
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Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
Pending
Application number
CN202011268544.8A
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Chinese (zh)
Inventor
罗忠
杨洪朋
康昊
武生茂
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Northeastern University China
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Northeastern University China
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Publication date
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Priority to CN202011268544.8A priority Critical patent/CN112485012A/en
Publication of CN112485012A publication Critical patent/CN112485012A/en
Pending legal-status Critical Current

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    • GPHYSICS
    • G01MEASURING; TESTING
    • G01MTESTING STATIC OR DYNAMIC BALANCE OF MACHINES OR STRUCTURES; TESTING OF STRUCTURES OR APPARATUS, NOT OTHERWISE PROVIDED FOR
    • G01M15/00Testing of engines
    • G01M15/14Testing gas-turbine engines or jet-propulsion engines
    • GPHYSICS
    • G01MEASURING; TESTING
    • G01MTESTING STATIC OR DYNAMIC BALANCE OF MACHINES OR STRUCTURES; TESTING OF STRUCTURES OR APPARATUS, NOT OTHERWISE PROVIDED FOR
    • G01M15/00Testing of engines
    • G01M15/02Details or accessories of testing apparatus
    • GPHYSICS
    • G01MEASURING; TESTING
    • G01MTESTING STATIC OR DYNAMIC BALANCE OF MACHINES OR STRUCTURES; TESTING OF STRUCTURES OR APPARATUS, NOT OTHERWISE PROVIDED FOR
    • G01M9/00Aerodynamic testing; Arrangements in or on wind tunnels
    • GPHYSICS
    • G01MEASURING; TESTING
    • G01MTESTING STATIC OR DYNAMIC BALANCE OF MACHINES OR STRUCTURES; TESTING OF STRUCTURES OR APPARATUS, NOT OTHERWISE PROVIDED FOR
    • G01M9/00Aerodynamic testing; Arrangements in or on wind tunnels
    • G01M9/06Measuring arrangements specially adapted for aerodynamic testing

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  • Physics & Mathematics (AREA)
  • General Physics & Mathematics (AREA)
  • Fluid Mechanics (AREA)
  • Chemical & Material Sciences (AREA)
  • Engineering & Computer Science (AREA)
  • Combustion & Propulsion (AREA)
  • Testing Of Engines (AREA)
  • Aerodynamic Tests, Hydrodynamic Tests, Wind Tunnels, And Water Tanks (AREA)

Abstract

The invention provides a solid rocket engine experiment table and a stress testing method, and relates to the technical field of solid rocket engines. The invention provides a simplified mechanism for simulating the test conditions of a solid rocket engine, and performs test research on the stress state of a nozzle structure in the working process, so that the nozzle design of the solid rocket engine is better optimized, and the tail nozzle is divided into a front-end tail nozzle and a rear-end tail nozzle, which is favorable for test, replacement and disassembly.

Description

Solid rocket engine experiment table and stress testing method
Technical Field
The invention belongs to the technical field of solid rocket engines, and particularly relates to a solid rocket engine experiment table and a stress testing method.
Background
The solid rocket engine consists of explosive column, combustion chamber, nozzle assembly, igniter, etc. The formula and forming process of the solid propellant, the design of the spray pipe, the material and manufacturing process of the spray pipe, and the material and manufacturing process of the shell are the most critical links, and the performance of the solid engine is directly influenced. The mixture of various components of the solid propellant formula can be prefabricated into a medicine column by a press-stretch forming process and then filled into the shell, and can also be directly cast against the wall in the shell. The housing directly serves as a combustion chamber. The jet pipe is used for discharging fuel gas at supersonic speed to generate thrust. As an important carrier of satellite launching, strategic weapons and the like, a solid rocket engine plays an important role in national economic and political life, so that the safety and various design indexes of the solid rocket engine are particularly emphasized, and particularly the stress state of a tail nozzle in the working process of the solid rocket engine is an important design parameter.
In the prior art, a solid rocket engine is often tested under complex test conditions in professional scientific research institutes, the academic institutions of colleges and universities are not beneficial to corresponding scientific research due to insufficient test conditions, a specific simplified structure is lacked for simulating the test conditions of the solid rocket engine, a tail nozzle of the conventional solid rocket engine is of an integrated structure, a part of materials are lost when the tail end of the inner surface of the tail nozzle is ablated by combustion flame after the operation is finished, the tail nozzle cannot be used continuously, if the integrated tail nozzle structure is adopted for a stress-strain test, the whole tail nozzle needs to be replaced after each test, and the cost is too high, so the solid rocket engine test bed and the stress testing method are provided.
Disclosure of Invention
In order to overcome the problems in the prior art, the invention provides a solid rocket engine experiment table and a stress testing method.
In order to achieve the purpose, the invention provides the following technical scheme: the utility model provides a solid rocket engine laboratory bench, includes wind-tunnel, first support, combustion chamber, first bolt, second bolt, front end tail nozzle, second bolt, third bolt, rear end tail nozzle, support ring, second support, base, strengthening rib and third support, first support links to each other through first bolt with combustion chamber one end, and just first support struts and is equipped with the hole with coaxial class internal diameter of combustion chamber, the combustion chamber other end passes through the second bolt and is connected with front end tail nozzle, front end tail nozzle passes through the third bolt and is connected with rear end tail nozzle. The rear end tail nozzle outer wall is located through the support ring, and the support ring is fixed in on the second supports, front end tail nozzle and rear end tail nozzle binding face are 45 and closely laminate, front end tail nozzle is unanimous with rear end tail nozzle length, front end tail nozzle inner surface is 45 isosceles triangle structures, rear end tail nozzle inner surface circular arc is tangent with front end tail nozzle 45 line directions.
Preferably, reinforcing ribs are arranged on two sides of the bottom of the first support.
Preferably, a wind tunnel is coaxially arranged on the front side of the combustion chamber and is fixed through a third support.
Preferably, the first support, the second support and the third support are all fixedly welded on the top of the base.
Preferably, the stress testing method comprises the following steps:
s1, attaching the strain gauge to the outer wall of the rear-end tail nozzle;
s2, starting the wind tunnel, and carrying out aerodynamic loading on the combustion chamber, the front-end tail nozzle and the rear-end tail nozzle;
s3, acquiring test data of the strain gauge, processing and analyzing the strain gauge data of the rear-end tail nozzle, and replacing different measuring points at equal intervals of 50mm to acquire the strain gauge data under the same loading; after the loading form is changed, the same test is continuously carried out at different measuring points;
and S4, repeating the steps, obtaining a plurality of groups of test parameters, and analyzing data to obtain a conclusion.
Compared with the prior art, the invention has the beneficial effects that:
the invention provides a simplified mechanism for simulating the test conditions of a solid rocket engine, and performs test research on the stress state of a nozzle structure in the working process, so that the nozzle design of the solid rocket engine is better optimized, and the tail nozzle is divided into a front-end tail nozzle and a rear-end tail nozzle, which is favorable for test, replacement and disassembly.
Drawings
FIG. 1 is a schematic front view of the present invention;
FIG. 2 is a schematic perspective view of the present invention;
in the figure: the device comprises a wind tunnel 1, a first support 2, a combustion chamber 3, a first bolt 4, a second bolt 5, a front end tail nozzle 6, a second bolt 7, a third bolt 8, a rear end tail nozzle 9, a support ring 10, a second support 11, a base 12, a reinforcing rib 13 and a third support 14.
Detailed Description
The present invention will be described in further detail with reference to the following drawings and examples. It should be understood that the specific embodiments described herein are merely illustrative of the invention and are not intended to limit the invention.
Referring to fig. 1-2, the present invention provides a technical solution: the utility model provides a solid rocket engine laboratory bench and stress test method, includes wind-tunnel 1, first support 2, combustion chamber 3, first bolt 4, second bolt 5, front end jet nozzle 6, second bolt 7, third bolt 8, rear end jet nozzle 9, support ring 10, second support 11, base 12, strengthening rib 13 and third support 14, its characterized in that: first support 2 links to each other through first bolt 4 with 3 one end of combustion chamber, and first support 2 sets up the hole with 3 coaxial equal internal diameters of combustion chamber, the 3 other ends of combustion chamber pass through second bolt 7 and are connected with front end jet nozzle 6, front end jet nozzle 6 passes through third bolt 8 and is connected with rear end jet nozzle 9, rear end jet nozzle 9 outer wall passes through support ring 10 location, and support ring 10 is fixed in on second supports 11, 2 bottom both sides of first support are equipped with strengthening rib 13, 3 coaxial wind-tunnel 1 that are equipped with of combustion chamber front side, and wind-tunnel 1 supports 14 fixedly through the third, first support 2, second support 11 and the equal fixed welding of third support 14 are in base 12 top.
The stress testing method comprises the following steps: s1, attaching the strain gauge to the outer wall of the rear-end tail nozzle 9; s2, starting the wind tunnel 1, and carrying out aerodynamic loading on the combustion chamber 3, the front end tail nozzle 6 and the rear end tail nozzle 9; s3, acquiring test data of the strain gauge; and S4, repeating the steps, obtaining a plurality of groups of test parameters, and analyzing data to obtain a conclusion.

Claims (5)

1. The utility model provides a solid rocket engine laboratory bench, includes wind-tunnel (1), first support (2), combustion chamber (3), first bolt (4), second bolt (5), front end tail nozzle (6), second bolt (7), third bolt (8), rear end tail nozzle (9), support ring (10), second support (11), base (12), strengthening rib (13) and third support (14), its characterized in that: the first support (2) is connected with one end of the combustion chamber (3) through a first bolt (4), the first support (2) is provided with a hole which is coaxial with the combustion chamber (3) and has the same inner diameter, the other end of the combustion chamber (3) is connected with the front end tail nozzle (6) through a second bolt (7), and the front end tail nozzle (6) is connected with the rear end tail nozzle (9) through a third bolt (8); rear end tail nozzle (9) outer wall passes through support ring (10) location, and support ring (10) are fixed in on second support (11) front end tail nozzle is 45 inseparable laminating with rear end tail nozzle binding face, front end tail nozzle (6) spray tube is unanimous with rear end tail nozzle (9) length, front end tail nozzle (6) inner surface is 45 isosceles triangle structures, rear end tail nozzle (9) inner surface circular arc is tangent with front end tail nozzle (6)45 line directions.
2. A solid-rocket engine test stand according to claim 1, wherein: reinforcing ribs (13) are arranged on two sides of the bottom of the first support (2).
3. A solid-rocket engine test stand according to claim 1, wherein: the front side of the combustion chamber (3) is coaxially provided with a wind tunnel (1), and the wind tunnel (1) is fixed through a third support (14).
4. A solid-rocket engine test stand according to claim 1, wherein: the first support (2), the second support (11) and the third support (14) are fixedly welded on the top of the base (12).
5. The method for testing the stress of a solid-rocket engine test stand according to any one of claims 1 to 4, wherein: the method comprises the following steps:
s1, attaching the strain gauge to the outer wall of the rear-end tail nozzle (9);
s2, starting the wind tunnel (1), and carrying out aerodynamic loading on the combustion chamber (3), the front end tail nozzle (6) and the rear end tail nozzle (9);
s3, acquiring test data of the strain gauge, processing and analyzing the strain gauge data of the rear-end tail nozzle (9), and replacing different measuring points at equal intervals of 50mm to acquire the strain gauge data under the same loading; after the loading form is changed, the same test is continuously carried out at different measuring points;
and S4, repeating the steps, obtaining a plurality of groups of test parameters, and analyzing data to obtain a conclusion.
CN202011268544.8A 2020-11-13 2020-11-13 Solid rocket engine experiment table and stress testing method Pending CN112485012A (en)

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Cited By (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN113063601A (en) * 2021-03-30 2021-07-02 大连理工大学 Aircraft auxiliary power unit jet-nozzle test system
CN113252353A (en) * 2021-04-06 2021-08-13 浙江蓝箭航天空间科技有限公司 Horizontal test method for electromechanical servo mechanism of carrier rocket and computer storage medium
CN113465933A (en) * 2021-06-29 2021-10-01 西安零壹空间科技有限公司 Internal pressure and external load composite static force testing device for solid rocket engine
CN118032259A (en) * 2024-04-09 2024-05-14 中国空气动力研究与发展中心高速空气动力研究所 Sub-transonic variable-angle concurrent direct-connection wind tunnel test engine bench and design method

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CN110566371A (en) * 2019-10-09 2019-12-13 湖南云顶智能科技有限公司 detachable rocket engine for test
CN110749536A (en) * 2019-10-16 2020-02-04 南京理工大学 Solid rocket engine thermal protection material ablation experimental device
CN110763469A (en) * 2019-11-22 2020-02-07 北京航天三发高科技有限公司 Engine test bed thrust measurement decides frame and thrust measurement rack thereof
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Cited By (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN113063601A (en) * 2021-03-30 2021-07-02 大连理工大学 Aircraft auxiliary power unit jet-nozzle test system
CN113252353A (en) * 2021-04-06 2021-08-13 浙江蓝箭航天空间科技有限公司 Horizontal test method for electromechanical servo mechanism of carrier rocket and computer storage medium
CN113252353B (en) * 2021-04-06 2023-09-22 浙江蓝箭航天空间科技有限公司 Carrier rocket electromechanical servo mechanism horizontal test method and computer storage medium
CN113465933A (en) * 2021-06-29 2021-10-01 西安零壹空间科技有限公司 Internal pressure and external load composite static force testing device for solid rocket engine
CN113465933B (en) * 2021-06-29 2024-03-29 西安零壹空间科技有限公司 Internal pressure and external load composite static force testing device of solid rocket engine
CN118032259A (en) * 2024-04-09 2024-05-14 中国空气动力研究与发展中心高速空气动力研究所 Sub-transonic variable-angle concurrent direct-connection wind tunnel test engine bench and design method

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Application publication date: 20210312