CN114151238A - Vertical weak-constraint cold-flow solid rocket engine test bed and pulse triggering experimental device and method - Google Patents
Vertical weak-constraint cold-flow solid rocket engine test bed and pulse triggering experimental device and method Download PDFInfo
- Publication number
- CN114151238A CN114151238A CN202111421651.4A CN202111421651A CN114151238A CN 114151238 A CN114151238 A CN 114151238A CN 202111421651 A CN202111421651 A CN 202111421651A CN 114151238 A CN114151238 A CN 114151238A
- Authority
- CN
- China
- Prior art keywords
- engine
- section
- test
- frame
- shell
- Prior art date
- 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.)
- Granted
Links
Images
Classifications
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02K—JET-PROPULSION PLANTS
- F02K9/00—Rocket-engine plants, i.e. plants carrying both fuel and oxidant therefor; Control thereof
- F02K9/96—Rocket-engine plants, i.e. plants carrying both fuel and oxidant therefor; Control thereof characterised by specially adapted arrangements for testing or measuring
Landscapes
- Engineering & Computer Science (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Testing Of Engines (AREA)
- Investigating Strength Of Materials By Application Of Mechanical Stress (AREA)
Abstract
A vertical weak-constraint cold-flow solid rocket engine test bed and a pulse triggering experimental device and method belong to the technical field of rocket engine testing, and comprise a base, a slide rail, a slide block, an axial safety limiting device, a rectangular steel pipe frame, a head support, a radial safety limiting device, a foot rest, a guide plate, a force hammer, a thrust frame, an air inlet pipe, a steady flow section, a testing engine shell, a tail jet pipe section and a perforated plate; one side of the rectangular steel pipe frame is fixed with a slide rail through a bolt and is fixed on the base together with the foot rest in a welding mode; a guide plate is arranged below the test section and welded on the base; the rectangular steel pipe jacking pipe is a top cover and is used for bearing the thrust of the test section and reinforcing the frame structure; the head support and the radial safety limiting device are fixed on the sliding block through bolts and are positioned through the axial safety limiting device; the thrust frame, the air inlet pipe, the flow stabilizing section, the test engine shell and the test engine spray pipe are connected in sequence through bolts and are arranged on the head support.
Description
Technical Field
The invention belongs to the technical field of rocket engine testing, and particularly relates to a vertical weak-constraint cold-flow solid rocket engine test bed, a pulse triggering experimental device and a pulse triggering experimental method.
Background
The unstable combustion of the solid rocket engine means that the pressure of a combustion chamber deviates from the rule predetermined by a designer to form transient pressure change. The high-energy charge is equipped in a solid rocket engine at present, so that the engine can work in a worse environment, the interior of the engine is exposed to a high-temperature and high-pressure environment, and the conditions of abnormal ballistic pressure in the engine, irregular shaking of a shell, deviation of an outer ballistic curve and even explosion can be caused by slight disturbance. And the flight state can not be completely reproduced due to the strong constraint action on the shell in the ground test run. For the inconsistency between the ground test and the flight test, the improvement of the ground test condition is urgently needed, so that the unstable combustion problem can be triggered and reproduced on the ground.
The mass system composed of the engine and the test frame can generate vibration under the impact of ignition and shutdown of the engine and the unstable combustion action in the whole working process. The existing test bed usually adopts multi-section strong constraint to fix the engine on the support, the multi-section strong constraint changes the original resonance frequency of the engine, inhibits the coupling relation between the structure of the engine and the internal instability, and has great influence on the modal test of unstable combustion.
Unstable combustion of a solid rocket engine is usually caused by nonlinear triggering of an inner trajectory or an outer trajectory, and mainly occurs in extreme working conditions of deflagration, nozzle blockage, maneuvering overload, nozzle swing and the like in the engine. How to map the nonlinear triggering condition of the aerial flight in the ground state is an input problem which is urgently needed to be solved by the ground test.
Compared with the traditional test bed, the weakly-constrained cold-flow solid rocket engine test bed can release the tail freedom degree of the engine, ensures the tail freedom degree of the engine and the reduction of the original resonance mode in a single-end fixing mode, provides a test method for the space-ground consistency of an unstable combustion test, and better reproduces the high-altitude real flight working condition. Meanwhile, the ground reproduction of the air flight condition is realized by using the method of internal ignition powder explosion and external force hammer knocking.
Disclosure of Invention
The invention aims to solve the problem that the ground test of an engine cannot reproduce the inconsistency of the sky and the ground of a high-altitude flight test, and provides a set of vertical weak-constraint cold-flow solid rocket engine test bed, a pulse triggering test device and a pulse triggering test method for the test method of the unstable combustion of the engine.
The purpose of the invention is realized by the following technical scheme:
the vertical weak constraint cold flow solid rocket engine test bed and pulse triggering experimental device and method comprise the following steps: the device comprises a base, a slide rail, a slide block, an axial safety limiting device, a top cover, a rectangular steel pipe frame, a head support, a radial safety limiting device, a foot rest, a guide plate, a force hammer, a thrust frame, an air inlet pipe, a flow stabilizing section, a test engine shell, a tail jet pipe section and a perforated plate; one side of the rectangular steel pipe frame is fixed with a slide rail through a bolt, is fixed on the base together with the foot rest in a welding mode, is connected with the base through the foot rest, and is provided with a guide plate below the rectangular steel pipe frame and is welded on the base; a top cover is installed on the top pipe of the rectangular steel pipe frame and used for bearing the thrust of the test section and reinforcing the frame structure; the head support is connected to the sliding rail through a sliding block, the head support and the radial safety limiting device are fixed on the sliding block through bolts, and the axial safety limiting device is axially installed; the thrust frame, the air inlet pipe and the steady flow section are sequentially connected through bolts, the test engine shell and the test engine tail jet pipe section are installed on the head support, the force hammer is installed on the base, the head of the engine combustion chamber is connected with the steady flow section flange through the flange, the steady flow section is fixedly supported on the head support, the engine combustion chamber is connected with the tail jet pipe section through the flange, and due to vertical clamping, the engine only bears axial force and has no radial bending moment; the flow stabilizing section is provided with a perforated plate, the front of the flow stabilizing section is connected with the head triaxial force thrust sensor through a thrust frame, the thrust of the engine can be tested, and the radial safety limiting device on the outer side of the tail of the engine is not in contact with the shell of the tested engine, so that the possible structural damage of the engine under the condition of extreme vibration is prevented, and the shaking range of the engine is limited.
The present invention may further comprise:
1. the perforated plate can not only reduce the speed and increase the pressure of high-speed gas entering through the sudden expansion of the head, so that the speed of the gas on the axial section after passing through the sieve plate is similar, but also isolate the combustion chamber from the cavity of the steady flow section, so that the pressure oscillation of the combustion chamber cannot be transmitted into the steady flow section.
2. The engine is connected with four pressure sensors through punching, and the rectifying section is connected with one pressure sensor through punching to obtain ballistic pressure data in the engine; engine vibration data is obtained by three acceleration sensors at the same axial position as the pressure sensors.
3. High-pressure nitrogen is introduced into the front end of the steady flow section of the engine head to simulate gas flow caused by working media generated by propellant combustion in a combustion chamber of a solid rocket engine, and the high-pressure nitrogen can enter the inside of the projectile body at uniform flow velocity and is sprayed out through the tail jet pipe section after being rectified by the perforated plate of the steady flow section.
4. The ignition explosive charge arranged in the test engine shell can realize point source excitation of an inner trajectory, and simulate inner trajectory pressure oscillation and shell vibration of the engine caused by internal pulse triggering due to deflagration in an engine combustion chamber; the force hammer can apply local acting force to the shell, and the acceleration sensor is matched to obtain acceleration response, so that the natural frequency of the engine is obtained, and the local impact load of the engine shell caused by sudden work of an overload or steering engine is simulated; pulse excitation is applied through ignition explosive package explosion, and the coupling relation of internal pressure oscillation frequency and structure oscillation is obtained through cooperation of a pressure sensor.
The invention has the beneficial effects that:
1. the vertical weak-constraint cold-flow solid rocket engine test bed provided by the invention has the characteristic of limiting the freedom degree of an engine to the minimum under the ground test condition, the stress characteristic of the free flight state of the engine is reproduced as much as possible, the freedom degree of the engine is released, and the weak-constraint free vibration can be realized.
2. The vertical weak constraint cold flow solid rocket engine test bed provided by the invention can adapt to different test models by replacing head supports with different sizes.
3. Compared with other test frames, the vertical weak-constraint cold-flow solid rocket engine test bed provided by the invention has the weak-constraint characteristic, has the advantages of simple structure, high reliability and the like, and has the advantage of multiple degrees of freedom of an engine compared with other multi-component test frames.
4. The pulse triggering experiment method matched with the vertical weak-constraint cold-flow solid rocket engine test bed has the characteristics of simple operation and strong realizability, and can test the natural vibration frequency of the sound cavity and the structure of the non-standard part by means of conventional experiment equipment.
5. The vertical weak-constraint cold-flow solid rocket engine test bed and the pulse triggering experiment method provided by the invention can trigger the phenomenon of unstable combustion of ballistic vibration and shell shaking in the engine, so that the engine can test whether design defects and problems exist on ground test without a flight test, and the unstable combustion phenomenon can be reproduced on the ground earlier.
Drawings
FIG. 1 is a general assembly drawing of a vertical weak constraint cold flow solid rocket engine test bed and a pulse triggering experimental device and method of the invention;
FIG. 2 is an assembly drawing of a support structure and a safety stop device of the vertical weak constraint cold flow solid rocket engine test bed and the pulse triggering experimental device and method of the present invention;
FIG. 3 is a test structure of a thrust frame, a steady flow section, an engine housing, a spray pipe and the like of the vertical weak constraint cold flow solid rocket engine test bed and the pulse triggering experimental device and method;
FIG. 4 is a sectional structure diagram of a steady flow section and an engine body of the vertical weak constraint cold flow solid rocket engine test bed and the pulse triggering experimental device and method.
Detailed Description
The invention is further described below with reference to the accompanying drawings.
According to the figures 2 to 4, the test bed and the pulse triggering experimental device and the method for the weakly-restricted cold-flow solid rocket engine comprise the following steps: the device comprises a base (1), a sliding rail (2), a sliding block (3), an axial safety limiting device (4), a top cover (5), a rectangular steel pipe frame (6), a head support (7), a radial safety limiting device (8), a foot rest (9), a guide plate (10), a force hammer (11), a thrust frame (12), an air inlet pipe (13), a steady flow section (14), a testing engine shell (17), a tail spray pipe section (19) and a perforated plate (20). The engine is characterized in that the base (1), the top cover (5), the rectangular steel pipe frame (6), the sliding rail (2) and the sliding block (3) are main bearing structures, and the axial degree of freedom of the engine can be reserved through the structures. The slide rail (2) and the rectangular steel pipe frame (6) are connected by welding. The radial safety limiting device (8) is divided into an upper part and a lower part which are connected through bolts, so that the tail end shaking range can be controlled when the engine shakes violently. The axial safety limiting device (4) is used for limiting the position of the engine in the axial direction. The head support (7) is an important supporting structure of the engine and is of a symmetrical structure, and the steady flow section (14) is connected and clamped through bolts, so that stability is guaranteed. The steady flow section (14) adopts a circular pipe with the wall thickness of 20mm and a head-tail flange structure. The rear part of the steady flow section (14) is welded with a porous plate (20), so that the effects of stably inputting gas and balancing the flow rate of the gas in the flow channel can be achieved, and meanwhile, the pressure response in the shell is ensured not to be transmitted to the steady flow section (14) in advance. Intake pipe (13) are a return bend, are connected with stationary flow section (14) through the welding mode, and intake pipe (13) one end is connected with gas supply system, and this pipeline section intercommunication gas supply system and engine, during equipment work, the high-pressure nitrogen gas that gas supply system provided flows into stationary flow section (14) through the intake pipe and stabilizes, reentrant engine is interior. The test engine shell (17) is a 2 mm-wall-thickness tapered tube which is wound by a T700 carbon fiber material, is a scaling model of a real engine, plays a role in maintaining the pressure stability in the engine, and is a main body structure of the engine. The head part is connected with the steady flow section (14) through a flange, and the tail part is connected with a test engine spray pipe (19) through a flange. The engine pressure measuring bases (18) are 5 in number, 1 is welded on the steady flow section (14), and the other 4 are respectively arranged at the front part, the middle part and the rear part of the shell (17) of the test engine and the end surface of the spray pipe (19) of the test engine and can be connected with a pressure sensor to measure the pressure in the engine. The force hammer (11) is an input device for testing a modal experiment of the engine shell (17), and external pulse excitation can be realized by knocking the engine through the handheld force hammer (11). The ignition explosive package (21) is an input device for pulse excitation in the engine, and black powder of the ignition explosive package (21) is ignited through an igniter to generate local pulse excitation so as to influence a flow field in the engine.
According to the figures 1 and 2, the engine model is obtained by adopting the conventional solid rocket engine scaling, and the carbon fiber composite material is selected as the test engine shell (17), so that the engine model has the characteristics of high strength and small mass. Engines with different diameters and lengths can be selected according to test items in actual tests. The main parts of the invention comprise: the engine testing device comprises an engine supporting frame, a testing engine main body, matched testing equipment and a pulse triggering experimental device. The motive support frame includes: the device comprises a base (1), a sliding rail (2), a sliding block (3), an axial safety limiting device (4), a top cover (5), a rectangular steel pipe frame (6), a head support (7), a radial safety limiting device (8), a foot rest (9) and a guide plate (10); the test engine body includes: the device comprises a thrust frame (12), an air inlet pipe (13), a steady flow section (14), a test engine shell (17), an engine pressure measuring base (18) and a tail jet pipe section (19); the supporting test equipment includes: an accelerometer (15), a head pressure measuring base (16); the pulse triggering experimental device comprises: an ignition explosive charge (21) and a hammer (11). The engine supporting frame supports the engine main body, the pulse triggering experiment device is used for conducting experiments, and experiment data are obtained through matched test equipment.
According to figure 2, the radial safety limiting device (8) and the head support (7) are connected to the sliding block on the sliding rail through bolts, the two devices can freely move on the sliding rail (2), the rectangular steel pipe frame (6) and the foot rest (9) are welded during assembly, the two devices are jointly installed on the base (1), the sliding block (3) is installed on the sliding rail (2) to guarantee the parallelism of the sliding rail, and the top cover (5) is connected with the tail end of the sliding rail through bolts. The axial safety limiting device (4) is connected with the rectangular steel pipe frame (6) through bolts, and the sliding block (3) is constrained in axial displacement. And then, the steady flow section (14) and the head support (7) are assembled and then connected with the slide block (3), and a radial safety limiting device (8) is installed. Finally, a guide plate (10) is installed.
According to fig. 3, the test structure is assembled and divided into 5 sections, namely a head thrust frame (12), an air inlet pipe (13), a steady flow section (14), an engine housing section (12) and a tail nozzle section (19). The air inlet pipe (13) is connected with the steady flow section (14) through welding, the rest sections are connected through flanges, a rubber ring is adopted for sealing, and the head thrust frame (12) is connected with the thrust sensor to measure thrust. The air inlet pipe (13) is connected with an air supply system through external threads to provide high-pressure high-flow gas. When the test is started, the gas supply valve is opened, gas flows into the flow stabilizing pipe section (14) through the gas inlet pipe (13) and enters the shell (17) of the test engine, and the gas expands through the spray pipe to do work and provide thrust. The head pressure measuring base (16) and the 3 engine pressure measuring bases (18) are connected with a pressure sensor through threads to measure the pressure in the engine, the accelerometer (15) is connected to the test engine shell (17) through a bonding mode, and the vibration acceleration of the test engine shell (17) is tested.
According to the figure 4, the head thrust frame (12), the air inlet pipe (13), the steady flow section (14), the engine shell section (12) and the tail spray pipe section (19) are in a half-sectional view, wherein the porous plate (20) is connected in the steady flow section (14) in a welding mode, and the ignition explosive bag (21) is connected at the center of the porous plate (20) through a thin line. The charge (22) is ethylene propylene diene monomer rubber, simulates the mechanical characteristics of an actual propellant, and the thickness of the charge can be changed to simulate the thickness of different propellants in different working stages of the engine.
The pulse triggering experiment method comprises an internal excitation experiment and an external excitation experiment: the internal excitation experiment is started, firstly, a valve of an air supply system is opened, high-pressure nitrogen is supplied to an engine, after the internal pressure of the engine is stabilized, an ignition explosive package (18) fixed in a combustion chamber shell is ignited through an electric igniter, and the energy generated by the ignition explosive package causes the internal pressure oscillation of the engine, so that the engine testing engine shell (17) is vibrated. The external excitation experiment is started, firstly, a valve of an air supply system is opened, high-pressure nitrogen is supplied to the engine, after the internal pressure of the engine is stabilized, the hammer (7) is used for knocking different response positions of the engine shell to generate pulse trigger vibration, and therefore vibration of the engine shell (17) is tested and even pressure oscillation is induced.
The above description is only a preferred embodiment of the present invention and is not intended to limit the present invention, and various modifications and changes may be made by those skilled in the art. Any modification, equivalent replacement, or improvement made within the spirit and principle of the present invention should be included in the protection scope of the present invention.
Claims (5)
1. Vertical weak restraint cold flow solid rocket engine test bed and pulse trigger experimental device and method, its characterized in that: the device comprises a base (1), a slide rail (2), a slide block (3), an axial safety limiting device (4), a top cover (5), a rectangular steel pipe frame (6), a head support (7), a radial safety limiting device (8), a foot rest (9), a guide plate (10), a force hammer (11), a thrust frame (12), an air inlet pipe (13), a steady flow section (14), a test engine shell (17), a tail spray pipe section (19) and a perforated plate (20); one side of the rectangular steel pipe frame (6) is fixed with the sliding rail (2) through a bolt, is fixed on the base (1) together with the foot rest (9) in a welding mode, is connected with the base (1) through the foot rest (9), and is provided with a guide plate (10) below the rectangular steel pipe frame (6) and is welded on the base (1); a top cover (5) is arranged on a top pipe of the rectangular steel pipe frame (6) and used for bearing the thrust of the test section and reinforcing the frame structure; the head support (7) is connected to the sliding rail (2) through the sliding block (3), the head support (7) and the radial safety limiting device (8) are fixed on the sliding block (3) through bolts, and the axial safety limiting device (4) is axially installed; the thrust frame (12), the air inlet pipe (13), the steady flow section (14), the test engine shell (17) and the test engine tail jet pipe section (19) are sequentially connected through bolts and are installed on the head support (7), the force hammer (11) is installed on the base (1), the head of an engine combustion chamber is connected with the steady flow section (14) through a flange, the steady flow section (14) is fixedly supported on the head support (7), the engine combustion chamber is connected with the tail jet pipe section (19) through the flange, and due to vertical clamping, the engine only bears axial force and has no radial bending moment; the flow stabilizing section (14) is provided with a porous plate (20), the front of the flow stabilizing section (14) is connected with a head triaxial force thrust sensor through a thrust frame (12), the thrust of an engine can be tested, a radial safety limiting device (8) on the outer side of the tail of the engine is not in contact with a tested engine shell (17), the possible structural damage of the engine under the limit vibration condition is prevented, and the shaking range of the engine is limited.
2. The vertical weak constraint cold flow solid rocket engine test bed and pulse triggering experimental device and method according to claim 1, characterized in that: the perforated plate (20) can not only reduce the speed and increase the pressure of high-speed gas entering through the sudden expansion of the head, so that the speed of the gas on the axial section after passing through the sieve plate is similar, but also isolate the combustion chamber from the cavity of the steady flow section, so that the pressure oscillation of the combustion chamber cannot be transmitted into the steady flow section.
3. The vertical weak constraint cold flow solid rocket engine test bed and pulse triggering experimental device and method according to claim 1, characterized in that: the engine is connected with four pressure sensors through punching, and the rectifying section is connected with one pressure sensor through punching to obtain ballistic pressure data in the engine; engine vibration data is obtained by three acceleration sensors at the same axial position as the pressure sensors.
4. The vertical weak constraint cold flow solid rocket engine test bed and pulse triggering experimental device and method according to claim 1, characterized in that: high-pressure nitrogen is introduced into the front end of a steady flow section (14) at the head of the engine to simulate gas flow caused by working media generated by propellant combustion in a combustion chamber of a solid rocket engine, and the high-pressure nitrogen can enter the inside of a projectile body at uniform flow velocity and is sprayed out through a tail jet pipe section (19) after being rectified by a perforated plate (20) of the steady flow section.
5. The vertical weak constraint cold flow solid rocket engine test bed and pulse triggering experimental device and method according to claim 1, characterized in that: the ignition explosive charge (21) arranged in the test engine shell (17) can realize point source excitation of an inner trajectory, and simulate inner trajectory pressure oscillation and shell vibration of an engine caused by internal pulse triggering due to detonation in an engine combustion chamber; the force hammer (11) can apply local acting force to the shell, and an acceleration sensor is matched to obtain acceleration response, so that the natural frequency of the engine is obtained, and the local impact load of the engine shell (17) caused by the sudden work of an overload or steering engine is simulated; pulse excitation is applied through explosion of the ignition explosive bag (21), and the internal pressure oscillation frequency and the coupling relation with structural oscillation are obtained through cooperation with the pressure sensor.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202111421651.4A CN114151238B (en) | 2021-11-26 | 2021-11-26 | Vertical weak-constraint cold-flow solid rocket engine test bed and pulse triggering experimental device and method |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202111421651.4A CN114151238B (en) | 2021-11-26 | 2021-11-26 | Vertical weak-constraint cold-flow solid rocket engine test bed and pulse triggering experimental device and method |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN114151238A true CN114151238A (en) | 2022-03-08 |
| CN114151238B CN114151238B (en) | 2022-12-13 |
Family
ID=80458047
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202111421651.4A Active CN114151238B (en) | 2021-11-26 | 2021-11-26 | Vertical weak-constraint cold-flow solid rocket engine test bed and pulse triggering experimental device and method |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN114151238B (en) |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN112610364A (en) * | 2020-12-29 | 2021-04-06 | 内蒙航天动力机械测试所 | Solid rocket engine elasticity weak constraint test stand |
Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN102818671A (en) * | 2012-08-16 | 2012-12-12 | 北京航空航天大学 | High-precision liquid or gas rocket engine thrust rack |
| CN110220712A (en) * | 2019-06-24 | 2019-09-10 | 西北工业大学 | A kind of rocket engine propulsion test device |
| CN110397520A (en) * | 2019-08-12 | 2019-11-01 | 西北工业大学 | Tilt adjustable rocket engine ground run rack |
| CN112432792A (en) * | 2020-11-25 | 2021-03-02 | 哈尔滨工程大学 | Solid rocket engine test frame based on magnetic suspension non-contact weak constraint |
| CN112610364A (en) * | 2020-12-29 | 2021-04-06 | 内蒙航天动力机械测试所 | Solid rocket engine elasticity weak constraint test stand |
-
2021
- 2021-11-26 CN CN202111421651.4A patent/CN114151238B/en active Active
Patent Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN102818671A (en) * | 2012-08-16 | 2012-12-12 | 北京航空航天大学 | High-precision liquid or gas rocket engine thrust rack |
| CN110220712A (en) * | 2019-06-24 | 2019-09-10 | 西北工业大学 | A kind of rocket engine propulsion test device |
| CN110397520A (en) * | 2019-08-12 | 2019-11-01 | 西北工业大学 | Tilt adjustable rocket engine ground run rack |
| CN112432792A (en) * | 2020-11-25 | 2021-03-02 | 哈尔滨工程大学 | Solid rocket engine test frame based on magnetic suspension non-contact weak constraint |
| CN112610364A (en) * | 2020-12-29 | 2021-04-06 | 内蒙航天动力机械测试所 | Solid rocket engine elasticity weak constraint test stand |
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN112610364A (en) * | 2020-12-29 | 2021-04-06 | 内蒙航天动力机械测试所 | Solid rocket engine elasticity weak constraint test stand |
| CN112610364B (en) * | 2020-12-29 | 2024-08-02 | 内蒙航天动力机械测试所 | Solid rocket engine elasticity weak constraint test frame |
Also Published As
| Publication number | Publication date |
|---|---|
| CN114151238B (en) | 2022-12-13 |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| Falempin et al. | Recent experimental results obtained on continuous detonation wave engine | |
| US5097743A (en) | Method and apparatus for zero velocity start ram acceleration | |
| CN114151238B (en) | Vertical weak-constraint cold-flow solid rocket engine test bed and pulse triggering experimental device and method | |
| CN109252982B (en) | Test method for nonlinear unstable combustion of solid rocket engine under overload condition | |
| CN110749445B (en) | Ramjet direct-connected test device utilizing detonation driving technology | |
| Morehead | Project morpheus main engine development and preliminary flight testing | |
| CN109611240B (en) | Mars detection attitude control engine rarefied incoming flow high-altitude simulation test system | |
| CN114109656B (en) | Horizontal weak-constraint cold-flow solid rocket engine test bed and pulse triggering method | |
| CN210422805U (en) | Large-scale solid rocket grain structural integrity test device | |
| KR102380171B1 (en) | Test Apparatus for Ignition Performance of Membrane Type Pulse Separation Device of Dual Pulse Rocket Motor at High Altitude | |
| Maslov et al. | High-enthalpy hot-shot wind tunnel with combined heating and stabilization of parameters | |
| Matsuoka et al. | Study on a rotary-valved four-cylinder pulse detonation rocket: six degree-of-freedom flight measurement | |
| Wiggins et al. | Rotating detonations through hydrogen-air and ethylene-air mixtures in hollow and flow-through combustors | |
| Hongru | Oxyhydrogen combustion and detonation driven shock tube | |
| CN113864087B (en) | Method for checking efficiency of solid rocket engine nozzle | |
| Whitside et al. | Low Mach number testing of a scramjet for access to space | |
| CN114607526A (en) | Impact type model engine for researching tangential unstable combustion of double-liquid-phase propellant | |
| Ursino et al. | Second-Generation Development of a Radial Rotating Detonation Engine | |
| Knauber | Thrust misalignments of fixed-nozzle solid rocket motors | |
| Redhal et al. | Fuel Injection Dynamics and Detonation Wave Interaction in Rectangular Channel | |
| Glaser et al. | A fundamental study on the acoustic behavior of pulse detonation engines | |
| BRUCKNER et al. | High-velocity modes of the thermally choked ram accelerator | |
| Kasahara et al. | Experimental investigation of momentum and heat transfer in pulse detonation rockets | |
| CN115014621B (en) | Thrust measuring device for ground test of continuous detonation engine | |
| Matsuoka et al. | Thrust performance of rotary-valved four-cylinder pulse detonation rocket engine |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| PB01 | Publication | ||
| PB01 | Publication | ||
| SE01 | Entry into force of request for substantive examination | ||
| SE01 | Entry into force of request for substantive examination | ||
| GR01 | Patent grant | ||
| GR01 | Patent grant |