CN113687013A - Device for shooting solid propellant combustion test under overload condition - Google Patents
Device for shooting solid propellant combustion test under overload condition Download PDFInfo
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- CN113687013A CN113687013A CN202110870416.9A CN202110870416A CN113687013A CN 113687013 A CN113687013 A CN 113687013A CN 202110870416 A CN202110870416 A CN 202110870416A CN 113687013 A CN113687013 A CN 113687013A
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- G—PHYSICS
- G01—MEASURING; TESTING
- G01N—INVESTIGATING OR ANALYSING MATERIALS BY DETERMINING THEIR CHEMICAL OR PHYSICAL PROPERTIES
- G01N31/00—Investigating or analysing non-biological materials by the use of the chemical methods specified in the subgroup; Apparatus specially adapted for such methods
- G01N31/12—Investigating or analysing non-biological materials by the use of the chemical methods specified in the subgroup; Apparatus specially adapted for such methods using combustion
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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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Abstract
The invention discloses a device for shooting a solid propellant combustion test under an overload condition, which comprises: the device comprises a buffer tank, a motion tube, a combustion mechanism and a solid propellant, wherein one end of the motion tube is an inlet, the other end of the motion tube is an outlet, the inlet is communicated with the outlet of the buffer tank, the outlet of the motion tube is provided with a ball valve, the combustion mechanism consists of a combustion chamber and a guide part which are fixedly connected with each other, the guide part is used for extending into the motion tube through the outlet end of the motion tube and moving outside the motion tube along the trend of the motion tube after being impacted by high-pressure gas of the buffer tank, the guide part, the combustion chamber and the motion tube are coaxially arranged, the solid propellant is arranged in the combustion chamber, and the combustion chamber is used for moving outside the motion tube after being pushed by the guide part, so that the solid propellant generates overload, and a high-speed camera can conveniently shoot the particle motion state of the solid propellant; the invention can overcome the Coriolis acceleration in the using process and shoot the short-time overload test condition of the solid propellant under the high pressure of the particle motion by using the high-speed camera.
Description
Technical Field
The invention belongs to the field of overload test systems, and particularly relates to a device for shooting a solid propellant combustion test under an overload condition.
Background
At present, the main means for researching the flow field and the thermal structure of the high-overload engine comprises theoretical analysis, numerical simulation and tests, wherein the theoretical analysis and the numerical simulation are complex in analysis and calculation engineering due to large data volume, and particularly, the simulation calculation is not easy in the complex environment of the high-performance rocket engine, so that the calculation result is possibly greatly different from the actual result.
Disclosure of Invention
The invention aims to provide a device for shooting a solid propellant combustion test under an overload condition, so as to solve the problem that the overload test of a solid rocket engine is difficult to simultaneously overcome the Coriolis acceleration and research the motion of a single particle.
The invention adopts the following technical scheme: an apparatus for imaging a solid propellant combustion test under overload conditions, comprising:
the inlet of the buffer tank is communicated with the external high-pressure gas tank, the outlet of the buffer tank is arranged on the side wall,
one end of the motion pipe is an inlet, the other end of the motion pipe is an outlet, the inlet of the motion pipe is communicated with the outlet of the buffer tank, the outlet of the motion pipe is provided with a ball valve,
the combustion mechanism, constitute by combustion chamber and the guide of mutual fixed connection, the guide is used for stretching into in the motion tube through the exit end of motion tube, and move outside the motion tube along the motion tube trend in the motion tube after receiving the high-pressure gas impact of buffer tank, guide and combustion chamber and the coaxial setting of motion tube, install solid propellant in the combustion chamber, the combustion chamber is used for receiving the thrust of guide after to move outside the motion tube, and then make solid propellant produce the overload, so that high-speed camera shoots the particle motion state of solid propellant.
Furthermore, the combustion chamber is composed of a circular front sealing plate, a columnar combustion cylinder and a circular rear sealing plate in sequence, a closed accommodating space is formed, the axis of the combustion cylinder and the axis of the moving pipe are overlapped, and the shooting opening is formed in the wall of the combustion cylinder.
Furthermore, the moving pipe is close to and is a front sealing plate, at least two supporting rods are fixedly connected to the front sealing plate, the direction of each supporting rod is parallel to the direction of the combustion cylinder, a propellant fixing disk and a thermocouple fixing disk are connected to each supporting rod in a threaded mode, the disk surfaces of the propellant fixing disk and the thermocouple fixing disk are perpendicular to the direction of each supporting rod, the central position of the propellant fixing disk is used for installing solid propellant, and a plurality of through holes used for installing thermocouples are formed in the central position of the thermocouple fixing disk.
Furthermore, a shooting port is formed in the side wall of the combustion chamber and used for shooting by a high-speed camera.
Furthermore, a sealing mechanism is arranged on the periphery of the combustion chamber and close to the shooting port, the sealing mechanism comprises a cover plate, an accommodating ring and a pressing plate,
the cover plate is provided with a through hole with the diameter smaller than that of the shooting opening, the through hole and the shooting opening are coaxially arranged,
the containing ring is annular and is coaxial with the shooting opening, the containing ring is fixedly connected with the side wall of the cover plate, the inner wall of the containing ring is provided with internal threads, the containing ring is internally used for placing glass,
the clamp plate is the ring form, and with shoot mouthful coaxial setting, be provided with on the outer wall of clamp plate with hold the internal thread matched with external screw thread of ring, the clamp plate is used for pressing glass in holding the ring for glass is sealed with the combustion chamber, and then makes things convenient for high-speed camera to see through the propellant burning condition of glass in to the combustion chamber and shoots.
Furthermore, the guide piece comprises a piston head and a guide rod which are fixedly connected with each other, the piston head is arranged close to the buffer tank, the axes of the piston head and the guide rod are overlapped with the axis of the movement pipe, one end of the guide rod is fixedly connected with the piston head, and the other end of the guide rod is fixedly connected with the front sealing plate.
Furthermore, a hydraulic buffer is fixedly arranged on one side of the combustion chamber, a cushion pad is fixedly connected to one side, away from the guide piece, of the rear sealing plate, and the hydraulic buffer is used for buffering the combustion chamber when the combustion chamber moves towards the direction away from the moving pipe.
Further, the slider is installed to the downside of combustion chamber, and then makes the combustion chamber pass through the slider and the slide rail cooperation that is located the below, and then fixes on the mount of downside, guarantees the steady motion of combustion chamber.
Further, a pressure sensor is mounted on the combustion cylinder.
Furthermore, an electrified electromagnet is fixedly connected at the outlet of the motion pipe.
The invention has the beneficial effects that: the invention can apply 5g of transverse or axial overload on the solid propellant, and can shoot the motion state of particles in the propellant when the particles are overloaded by a high-speed camera; the applied overload of the invention has no influence of Coriolis acceleration; according to the invention, the overload combustion of the solid propellant can be finely researched through the result shot by the high-speed camera; the invention can overcome the Coriolis acceleration in the using process, and uses a high-speed camera to shoot the short-time overload test condition of the solid propellant under the high pressure of the particle motion, so that the transverse overload can be simulated and the micro motion mechanism of the particles can be researched.
Drawings
FIG. 1 is a schematic structural view of the present invention;
FIG. 2 is a schematic structural view of the combustion mechanism of the present invention;
FIG. 3 is a cross-sectional view of the combustion can of the present invention;
fig. 4 is a schematic structural diagram of the sealing mechanism of the present invention.
Wherein: 1. a buffer tank; 2. a motion tube; 3. a combustion mechanism; 4. a combustion chamber; 5. a guide member; 6. a solid propellant; 7. a shooting port; 8. a front closing plate; 9. a combustion can; 10. a rear closing plate; 11. a support bar; 12. a propellant fixing disk; 13. a thermocouple fixing disc; 14. a hydraulic buffer; 15. a cushion pad; 16. a sealing mechanism; 17. a cover plate; 18. a containment ring; 19. and (7) pressing a plate.
Detailed Description
The present invention will be described in detail below with reference to the accompanying drawings and specific embodiments.
The invention discloses a device for shooting a solid propellant combustion test under an overload condition, which comprises a buffer tank 1, a moving pipe 2 and a combustion mechanism 3, wherein an inlet of the buffer tank 1 is communicated with an external high-pressure gas tank, an outlet of the buffer tank 1 is arranged on the side wall, one end of the moving pipe 2 is an inlet, the other end of the moving pipe 2 is an outlet, the inlet of the moving pipe 2 is communicated with the outlet of the buffer tank 1, and a ball valve is arranged at the outlet of the moving pipe 2.
As shown in fig. 2, the combustion mechanism 3 is composed of a combustion chamber 4 and a guide member 5, which are fixedly connected with each other, the guide member 5 is used for extending into the motion tube 2 through the outlet end of the motion tube 2, and moving outside the motion tube 2 along the moving direction of the motion tube 2 in the motion tube 2 after being impacted by the high-pressure gas in the buffer tank 1, the guide member 5 and the combustion chamber 4 are coaxially arranged with the motion tube 2, a solid propellant 6 is installed in the combustion chamber 4, the combustion chamber 4 is used for moving outside the motion tube 2 after being pushed by the guide member 5, and further the solid propellant 6 is overloaded, so that the high-speed camera can conveniently move the particles of the solid propellant 6.
The side wall of the combustion chamber 4 is provided with a shooting port 7, the shooting port 7 is used for shooting by a high-speed camera, the combustion chamber 4 sequentially comprises a circular front sealing plate 8, a columnar combustion barrel 9 and a circular rear sealing plate 10, a closed accommodating space is formed, the axis of the combustion barrel 9 and the axis of the motion pipe 2 coincide with each other, and the shooting port 7 is arranged on the barrel wall of the combustion barrel 9.
As shown in fig. 4, a sealing mechanism 16 is arranged at the periphery of the combustion chamber 4 and near the shooting port 7, the sealing mechanism 16 includes a cover plate 17, a containing ring 18 and a pressing plate 19, a through hole with a diameter smaller than that of the shooting port 7 is formed in the cover plate 17, the through hole and the shooting port 7 are coaxially arranged, the containing ring 18 is in a circular ring shape and is coaxially arranged with the shooting port 7, the containing ring 18 is fixedly connected with the side wall of the cover plate 17, an internal thread is arranged on the inner wall of the containing ring 18, the containing ring 18 is internally used for placing glass, the pressing plate 19 is in a circular ring shape and is coaxially arranged with the shooting port 7, an external thread matched with the internal thread of the containing ring 18 is arranged on the outer wall of the pressing plate 19, and the pressing plate 19 is used for pressing the glass into the containing ring 18, so that the combustion chamber 4 is sealed by the glass, and further a high-speed camera can shoot the propellant combustion condition in the combustion chamber 4 through the glass.
As shown in fig. 3, a front seal plate 8 is arranged near the moving pipe 2, at least two support rods 11 are fixedly connected to the front seal plate 8, the direction of each support rod 11 is parallel to the direction of the combustion cylinder 9, a propellant fixing plate 12 and a thermocouple fixing plate 13 are connected to each support rod 11 in a threaded manner, the disc surfaces of the propellant fixing plate 12 and the thermocouple fixing plate 13 are perpendicular to the directions of the support rods 11, the central position of the propellant fixing plate 12 is used for mounting the solid propellant 6, a plurality of through holes for mounting thermocouples are formed in the central position of the thermocouple fixing plate 13, the head of each thermocouple extends into the thermocouple fixing plate 13 from one side of the through hole, the head of each thermocouple is flush with the thermocouple fixing plate 13, the through holes are filled with AB glue to fix the thermocouple, and the back of the thermocouple fixing plate 13 is prevented from shaking by using a transparent adhesive tape.
A hydraulic buffer 14 is fixedly arranged on one side of the combustion chamber 4, the type of the hydraulic buffer is preferably HYD-yqz95-100, a buffer cushion 15 is fixedly connected on one side of the rear closing plate 10 far away from the guide piece 5, and the hydraulic buffer 14 is used for buffering the combustion chamber 4 when the combustion chamber 4 moves towards the direction far away from the moving pipe 2. Because the designed overload amount of the invention reaches 5g, the weight of the combustion mechanism 3 is 43kg, the test is finished, namely the speed of the combustion mechanism 3 is very high after the observation is finished, the combustion mechanism 3 needs to be stopped in a very short time, the combustion mechanism 3 can be subjected to a very large impact force, the hydraulic buffer 14 needs to be used for buffering, and the buffer cushion 15 arranged on the rear sealing plate 10 can protect the rear sealing plate 10 from being damaged by the impact force in the buffering process.
The slider is installed to the downside of combustion chamber 4, and then makes combustion chamber 4 pass through the slider and the slide rail cooperation that is located the below, and then fixes on the mount of downside, guarantees the steady motion of combustion chamber 4. The sliding block and the sliding rail arranged below play a role in guiding and supporting, namely, the combustion mechanism 3 can only move along the axial direction; the combustion mechanism 3 is supported and bears the weight of the combustion mechanism 3 in the vertical direction.
The combustion cylinder 9 is provided with a pressure sensor. In this way, the pressure inside the combustion chamber 4 can be measured and collected during the test, and the pressure data is used for post-test data processing.
The guide piece 5 consists of a piston head and a guide rod which are fixedly connected with each other, the piston head is arranged close to the buffer tank 1, the axes of the piston head and the guide rod are overlapped with the axis of the moving pipe 2, one end of the guide rod is fixedly connected with the piston head, and the other end of the guide rod is fixedly connected with the front sealing plate 8. The length and diameter of the guide rods determine the weight of the combustion mechanism 3, and the guide rods are small in diameter in order to reduce the weight of the combustion mechanism 3 as much as possible, so that four reinforcing ribs are arranged to reinforce the structure.
The outlet of the motion pipe 2 is fixedly connected with an electrified electromagnet, the electromagnet is in a hollow circular ring shape, the axis of the electromagnet coincides with the axis of the motion pipe 2, and a tester can adjust the overload value of the combustion mechanism 3 according to the requirement by arranging the electromagnet. Without this electromagnet, when the moving tube 2 is filled with gas, the combustion means 3 is immediately pushed by the gas and cannot reach the overload value predetermined by the tester.
The invention can apply 5g of transverse or axial overload on the solid propellant 6, and can shoot the motion state of particles in the propellant when the particles are overloaded by a high-speed camera; the applied overload of the invention has no influence of Coriolis acceleration; according to the invention, the overload combustion of the solid propellant 6 can be studied finely according to the result shot by the high-speed camera; the invention can overcome the Coriolis acceleration and shoot the short-time overload test condition of the solid propellant 6 under the high pressure of the particle motion by using the high-speed camera in the using process, can simulate the transverse overload and research the micro motion mechanism of the particles, avoids the Coriolis acceleration influence brought by the rotation test, can develop the propellant combustion test, and is used for combustion speed measurement and particle size collection.
The working process of the invention is as follows:
closing the ball valve, electrifying the electromagnet, filling high-pressure gas into the buffer tank 1 by utilizing an external high-pressure gas tank, keeping the buffer tank 1 in a sealed state, enabling the high-pressure gas to enter the buffer tank 1,
after the pressure of the buffer tank 1 reaches a preset value, the ball valve is opened to ensure that high-pressure gas completely enters the combustion chamber 4,
when the pressure sensor connected with the combustion chamber 4 detects that the pressure in the combustion chamber 4 is unchanged, the high-speed camera is turned on, the electromagnet is turned off to supply power, at the moment, the piston head of the guide piece 5 is pushed by high-pressure gas to start moving,
at the end of the movement of the combustion chamber 4, the cushion pad 15 comes into contact with the hydraulic shock absorber 14 and pushes the hydraulic shock absorber 14, so that the combustion chamber 4 is rapidly decelerated, the movement of the combustion chamber 4 is stopped, and the test is completed.
The above description is only for the purpose of illustrating the preferred embodiments of the present invention and is not to be construed as limiting the invention, and any modifications, equivalents, improvements and the like that fall within the spirit and principle of the present invention are intended to be included therein.
Claims (10)
1. An apparatus for imaging a solid propellant combustion test under overload conditions, comprising:
an inlet of the buffer tank (1) is communicated with an external high-pressure gas tank, an outlet of the buffer tank is arranged on the side wall,
one end of the motion pipe (2) is an inlet, the other end of the motion pipe is an outlet, the inlet of the motion pipe is communicated with the outlet of the buffer tank (1), the outlet of the motion pipe is provided with a ball valve,
the combustion mechanism (3) comprises combustion chamber (4) and guide (5) that mutual fixed connection, guide (5) are used for stretching into in the motion pipe (2) through the exit end of motion pipe (2) to move outside motion pipe (2) along motion pipe (2) trend in motion pipe (2) after receiving the high-pressure gas impact of buffer tank (1), guide (5) and combustion chamber (4) and motion pipe (2) coaxial arrangement, install solid propellant (6) in combustion chamber (4), combustion chamber (4) are used for receiving the thrust of guide (5) to move outside motion pipe (2), and then make solid propellant (6) produce the overload to the particle motion state of solid propellant (6) is shot to the high-speed camera.
2. The device for shooting the solid propellant combustion test under the overload condition according to the claim 1 is characterized in that the combustion chamber (4) is composed of a circular front closing plate (8), a cylindrical combustion cylinder (9) and a circular rear closing plate (10) in sequence, and forms a closed accommodating space, the axis of the combustion cylinder (9) and the axis of the moving pipe (2) are coincident with each other, and the shooting port (7) is arranged on the wall of the combustion cylinder (9).
3. The device for shooting the solid propellant combustion test under the overload condition according to claim 2, wherein a front sealing plate (8) is arranged close to the moving pipe (2), at least two supporting rods (11) are fixedly connected to the front sealing plate (8), the direction of each supporting rod (11) is parallel to the direction of the combustion cylinder (9), a propellant fixing plate (12) and a thermocouple fixing plate (13) are connected to each supporting rod (11) in a threaded manner, the disc surfaces of the propellant fixing plate (12) and the thermocouple fixing plate (13) are perpendicular to the direction of each supporting rod (11), the central position of the propellant fixing plate (12) is used for installing the solid propellant (6), and a plurality of through holes for installing thermocouples are formed in the central position of the thermocouple fixing plate (13).
4. The device for shooting the solid propellant combustion test under the overload condition according to claim 3, wherein a shooting port (7) is formed in the side wall of the combustion chamber (4), and the shooting port (7) is used for shooting by a high-speed camera.
5. Device for shooting solid propellant combustion test under overload condition according to claim 3, characterized in that the periphery of the combustion chamber (4) near the shooting mouth (7) is provided with a sealing mechanism (16), the sealing mechanism (16) comprises a cover plate (17), a containing ring (18) and a pressure plate (19),
the cover plate (17) is provided with a through hole with the diameter smaller than that of the shooting port (7), the through hole and the shooting port (7) are coaxially arranged,
the containing ring (18) is annular and is coaxially arranged with the shooting port (7), the containing ring (18) is fixedly connected with the side wall of the cover plate (17), inner threads are arranged on the inner wall of the containing ring (18), glass is placed in the containing ring (18),
the clamp plate (19) is the ring form, and with shoot mouthful (7) coaxial setting, be provided with on the outer wall of clamp plate (19) and hold the internal thread matched with external screw thread of ring (18), clamp plate (19) are used for pressing glass in holding ring (18) for glass is sealed with combustion chamber (4), and then makes things convenient for high-speed camera to see through the propellant burning condition of glass in to combustion chamber (4) and shoots.
6. The device for shooting the solid propellant combustion test under the overload condition is characterized in that the guide piece (5) consists of a piston head and a guide rod which are fixedly connected with each other, the piston head is arranged close to the buffer tank (1), the axes of the piston head and the guide rod are coincided with the axis of the moving pipe (2), one end of the guide rod is fixedly connected with the piston head, and the other end of the guide rod is fixedly connected with the front sealing plate (8).
7. The device for shooting the solid propellant combustion test under the overload condition is characterized in that a hydraulic buffer (14) is fixedly arranged on one side of the combustion chamber (4), a buffer pad (15) is fixedly connected on one side, far away from the guide piece (5), of the rear sealing plate (10), and the hydraulic buffer (14) is used for buffering the combustion chamber (4) when the combustion chamber (4) moves towards the direction far away from the moving pipe (2).
8. The device for shooting the solid propellant combustion test under the overload condition is characterized in that a sliding block is installed on the lower side of the combustion chamber (4), so that the combustion chamber (4) is matched with a sliding rail located below through the sliding block and then fixed on a fixing frame on the lower side, and the stable movement of the combustion chamber (4) is guaranteed.
9. Device for shooting solid propellant combustion test under overload condition according to claim 8 characterized by that the combustion cylinder (9) is equipped with a pressure sensor.
10. Device for recording the combustion test of solid propellants under overload conditions according to claim 9, characterized in that an energized electromagnet is fixedly connected to the outlet of the moving pipe (2).
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| CN202110870416.9A CN113687013B (en) | 2021-07-30 | 2021-07-30 | Device for shooting solid propellant combustion test under overload condition |
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| CN202110870416.9A CN113687013B (en) | 2021-07-30 | 2021-07-30 | Device for shooting solid propellant combustion test under overload condition |
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Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN114965856A (en) * | 2022-05-23 | 2022-08-30 | 西安近代化学研究所 | Propellant combustion flame image acquisition device and observation system under rotation overload condition |
Citations (26)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| GB722706A (en) * | 1950-05-12 | 1955-01-26 | Soc Et Propulsion Par Reaction | Improvements in and relating to rockets |
| GB873670A (en) * | 1959-05-18 | 1961-07-26 | United Aircraft Corp | Improvements relating to solid propellant rockets |
| FR1558482A (en) * | 1967-12-22 | 1969-02-28 | ||
| DE3118789A1 (en) * | 1980-05-13 | 1982-02-11 | Nissan Motor Co., Ltd., Yokohama, Kanagawa | Solid propellant rocket engine with variable thrust |
| US4409821A (en) * | 1981-08-10 | 1983-10-18 | The United States Of America As Represented By The Secretary Of The Navy | Solid propellant measurement system |
| GB8506956D0 (en) * | 1984-03-27 | 1985-04-24 | British Aerospace | Rockets & motors |
| EP0242161A2 (en) * | 1986-04-14 | 1987-10-21 | Hercules Incorporated | Process for installing liner in pressure vessel |
| EP0321102A2 (en) * | 1987-12-16 | 1989-06-21 | General Electric Company | Liquid propellant weapon system |
| AU8535291A (en) * | 1991-09-04 | 1993-04-05 | Royal Ordnance Plc | The initiation of propellants |
| EP0859143A1 (en) * | 1997-02-12 | 1998-08-19 | Primex Technologies, Inc. | Single stage regulated bootstrap pressurization system |
| US5909299A (en) * | 1997-04-28 | 1999-06-01 | Sheldon, Jr.; L. Philip | Microsatellite system for high-volume orbital telemetry |
| US20100038565A1 (en) * | 2008-08-12 | 2010-02-18 | Honeywell International Inc. | Propellant gas control valve |
| CN102032987A (en) * | 2010-12-14 | 2011-04-27 | 西北工业大学 | Experiment device for researching jet atomizing characteristic of jet nozzle |
| CN104374864A (en) * | 2014-10-30 | 2015-02-25 | 西北工业大学 | Testing device for burning speed of propellant under tensile state |
| CN104596768A (en) * | 2015-01-13 | 2015-05-06 | 浙江大学 | Device for testing ignition combustion characteristics and propulsive performance of solid fuel micro-thruster |
| EP2898281A1 (en) * | 2012-09-19 | 2015-07-29 | Krauss-Maffei Wegmann GmbH & Co. KG | Propellant charge loader, weapon and method for loading propellant charges |
| CN106197175A (en) * | 2016-08-03 | 2016-12-07 | 中北大学 | Propellant charge strain and displacement integrated measurer under high overload |
| CN108169080A (en) * | 2017-11-21 | 2018-06-15 | 西北工业大学 | Solid propellant aluminium combustion measurement apparatus and method based on coaxial digital holography method |
| CN108593837A (en) * | 2018-06-08 | 2018-09-28 | 中国科学技术大学 | A kind of solid propellant high-pressure combustion characterisitic parameter measuring apparatus with observation window |
| CN108680700A (en) * | 2018-06-21 | 2018-10-19 | 西安交通大学 | The experimental system of energetic material crystal auto-ignition under a kind of observation Impulsive load |
| KR101965579B1 (en) * | 2017-10-31 | 2019-04-04 | 주식회사 한화 | Conbustion test apparatus of rocket engine and thrust measurement method of rocket engine using the same |
| CN109708145A (en) * | 2019-01-29 | 2019-05-03 | 北京理工大学 | For measuring the visualization high-pressure burner of propellant burning rate under more placement angles |
| CN110596301A (en) * | 2019-10-14 | 2019-12-20 | 西安近代化学研究所 | Test engine and test method for combustion of double-base propellant in different overload directions |
| CN111208255A (en) * | 2020-02-24 | 2020-05-29 | 北京理工大学 | Visual high-pressure burning rate instrument and method for multiple solid propellant drug strips |
| CN112526058A (en) * | 2020-11-04 | 2021-03-19 | 东南大学 | Small-thrust solid propellant grain combustion and propulsion performance detection test device |
| CN112666309A (en) * | 2021-02-04 | 2021-04-16 | 中国人民解放军国防科技大学 | High-pressure combustor experimental system and visual high-pressure combustor |
-
2021
- 2021-07-30 CN CN202110870416.9A patent/CN113687013B/en active Active
Patent Citations (27)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| GB722706A (en) * | 1950-05-12 | 1955-01-26 | Soc Et Propulsion Par Reaction | Improvements in and relating to rockets |
| GB873670A (en) * | 1959-05-18 | 1961-07-26 | United Aircraft Corp | Improvements relating to solid propellant rockets |
| FR1558482A (en) * | 1967-12-22 | 1969-02-28 | ||
| GB1217280A (en) * | 1967-12-22 | 1970-12-31 | Nord Aviation | Adjustment device for the flow of a liquid propellant into t hypergolic reaction system |
| DE3118789A1 (en) * | 1980-05-13 | 1982-02-11 | Nissan Motor Co., Ltd., Yokohama, Kanagawa | Solid propellant rocket engine with variable thrust |
| US4409821A (en) * | 1981-08-10 | 1983-10-18 | The United States Of America As Represented By The Secretary Of The Navy | Solid propellant measurement system |
| GB8506956D0 (en) * | 1984-03-27 | 1985-04-24 | British Aerospace | Rockets & motors |
| EP0242161A2 (en) * | 1986-04-14 | 1987-10-21 | Hercules Incorporated | Process for installing liner in pressure vessel |
| EP0321102A2 (en) * | 1987-12-16 | 1989-06-21 | General Electric Company | Liquid propellant weapon system |
| AU8535291A (en) * | 1991-09-04 | 1993-04-05 | Royal Ordnance Plc | The initiation of propellants |
| EP0859143A1 (en) * | 1997-02-12 | 1998-08-19 | Primex Technologies, Inc. | Single stage regulated bootstrap pressurization system |
| US5909299A (en) * | 1997-04-28 | 1999-06-01 | Sheldon, Jr.; L. Philip | Microsatellite system for high-volume orbital telemetry |
| US20100038565A1 (en) * | 2008-08-12 | 2010-02-18 | Honeywell International Inc. | Propellant gas control valve |
| CN102032987A (en) * | 2010-12-14 | 2011-04-27 | 西北工业大学 | Experiment device for researching jet atomizing characteristic of jet nozzle |
| EP2898281A1 (en) * | 2012-09-19 | 2015-07-29 | Krauss-Maffei Wegmann GmbH & Co. KG | Propellant charge loader, weapon and method for loading propellant charges |
| CN104374864A (en) * | 2014-10-30 | 2015-02-25 | 西北工业大学 | Testing device for burning speed of propellant under tensile state |
| CN104596768A (en) * | 2015-01-13 | 2015-05-06 | 浙江大学 | Device for testing ignition combustion characteristics and propulsive performance of solid fuel micro-thruster |
| CN106197175A (en) * | 2016-08-03 | 2016-12-07 | 中北大学 | Propellant charge strain and displacement integrated measurer under high overload |
| KR101965579B1 (en) * | 2017-10-31 | 2019-04-04 | 주식회사 한화 | Conbustion test apparatus of rocket engine and thrust measurement method of rocket engine using the same |
| CN108169080A (en) * | 2017-11-21 | 2018-06-15 | 西北工业大学 | Solid propellant aluminium combustion measurement apparatus and method based on coaxial digital holography method |
| CN108593837A (en) * | 2018-06-08 | 2018-09-28 | 中国科学技术大学 | A kind of solid propellant high-pressure combustion characterisitic parameter measuring apparatus with observation window |
| CN108680700A (en) * | 2018-06-21 | 2018-10-19 | 西安交通大学 | The experimental system of energetic material crystal auto-ignition under a kind of observation Impulsive load |
| CN109708145A (en) * | 2019-01-29 | 2019-05-03 | 北京理工大学 | For measuring the visualization high-pressure burner of propellant burning rate under more placement angles |
| CN110596301A (en) * | 2019-10-14 | 2019-12-20 | 西安近代化学研究所 | Test engine and test method for combustion of double-base propellant in different overload directions |
| CN111208255A (en) * | 2020-02-24 | 2020-05-29 | 北京理工大学 | Visual high-pressure burning rate instrument and method for multiple solid propellant drug strips |
| CN112526058A (en) * | 2020-11-04 | 2021-03-19 | 东南大学 | Small-thrust solid propellant grain combustion and propulsion performance detection test device |
| CN112666309A (en) * | 2021-02-04 | 2021-04-16 | 中国人民解放军国防科技大学 | High-pressure combustor experimental system and visual high-pressure combustor |
Non-Patent Citations (6)
| Title |
|---|
| GLOTOV O G等: "Evolution of aluminum agglomerates moving in combustion products of model solid propellant", 《INTERNATIONAL JOURNAL OF ENERGETIC MATERIALS AND CHEMICAL PROPULSION》 * |
| JIANG LI等: "Combustion characteristics of solid propellants under high-temperature dense-particle erosion conditions", 《COMBUSTION AND FLAME》 * |
| TSANGALIS C等: "Fluid-structure interaction modelling of propellant combustion", 《ANZIAM JOURNAL》 * |
| 刘佩进等: "固体火箭发动机燃烧不稳定研究进展与展望", 《推进技术》 * |
| 刘鑫等: "复合推进剂中铝燃烧实验研究", 《推进技术》 * |
| 赵亚芹等: "横向过载条件下的推进剂燃速预示", 《四川兵工学报》 * |
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN114965856A (en) * | 2022-05-23 | 2022-08-30 | 西安近代化学研究所 | Propellant combustion flame image acquisition device and observation system under rotation overload condition |
| CN114965856B (en) * | 2022-05-23 | 2024-03-26 | 西安近代化学研究所 | Propellant burning flame image acquisition device and observation system under rotation overload condition |
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