CN112161813A - Mobile micro-friction solid rocket engine thrust measurement system and installation method thereof - Google Patents
Mobile micro-friction solid rocket engine thrust measurement system and installation method thereof Download PDFInfo
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- CN112161813A CN112161813A CN202010951899.0A CN202010951899A CN112161813A CN 112161813 A CN112161813 A CN 112161813A CN 202010951899 A CN202010951899 A CN 202010951899A CN 112161813 A CN112161813 A CN 112161813A
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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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- 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
- G01M15/02—Details or accessories of testing apparatus
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- Testing Of Devices, Machine Parts, Or Other Structures Thereof (AREA)
- Force Measurement Appropriate To Specific Purposes (AREA)
Abstract
The invention relates to a thrust measurement system of a mobile micro-friction solid rocket engine and an installation method thereof, wherein the measurement system consists of a fixed frame, a movable frame, a support frame, an engine, an embracing ring, a transition frame, a force measuring assembly, a force bearing pier and a mandril; the movable frame and the bearing pier are both fixed on the fixed frame through bolts, the support frame is fixed on the movable frame through bolts, and the embracing ring is connected on the support frame; a top rod is fixed at the front end of the bearing pier through a bolt, and the rear end of the bearing pier is connected with a force measuring component; the rear end of the force measuring assembly is connected with a transition frame, and the transition frame is fixedly connected with the front skirt of the engine through bolts. The device's overall structure has saved normal position calibrating device, and the structure is compared traditional fixed leaf spring connection structure simpler, and the precision is also higher.
Description
Technical Field
The invention relates to a thrust measuring system of a mobile micro-friction solid rocket engine and an installation method thereof, belonging to the technical field of solid rocket engines.
Background
The solid rocket engine ground test is an irreversible, high-cost, high-risk test. The engine has short working time, large amount of information to be acquired, and high precision required by process control and key parameters. The thrust test of the solid rocket engine is the most important link in the ground test, and the test frame is a key device for the thrust test in the thrust test and has great influence on the test precision of the engine thrust, the transient thrust, the negative thrust and the like.
At present, the test frame with mature technology in China is mainly a fixed plate spring type test frame. The plate spring is an elastic constraint element of the test stand and has good elastic resistance repeatability. However, the plate spring type test frame has the following disadvantages:
1. the friction force of the plate spring is a variable value and generally changes along with the change of the mass of the engine, so that the test precision is influenced;
2. during testing, the plate spring is in a destabilization state, so that the testing precision is influenced;
3. the lateral rigidity of the plate spring is relatively weak, and the phenomenon of torsional deformation occurs, so that the test precision is influenced;
4. generally, 4 leaf springs are adopted in connection, but the damping of each leaf spring is anisotropic;
5. a test frame connected with a common plate spring needs a matched in-situ calibration device.
Disclosure of Invention
In order to overcome the difficulties, the invention provides a thrust measuring system of a mobile micro-friction solid rocket engine.
The invention relates to a thrust measurement system of a movable micro-friction solid rocket engine, which consists of a fixed frame, a movable frame, a support frame, an engine, an embracing ring, a transition frame, a force measurement assembly, a force bearing pier and a mandril; the movable frame and the bearing pier are both fixed on the fixed frame through bolts, the support frame is fixed on the movable frame through bolts, and the embracing ring is connected on the support frame; a top rod is fixed at the front end of the bearing pier through a bolt, and the rear end of the bearing pier is connected with a force measuring component; the rear end of the force measuring assembly is connected with a transition frame, and the transition frame is fixedly connected with the front skirt of the engine through bolts.
Furthermore, a bearing pier in the thrust measurement system of the mobile micro-friction solid rocket engine is an integral workpiece, and the inner structure of the bearing pier has the consistency of the center height and the coaxiality of positioning holes; the centering piece is centered with the movable frame and then fixed by a bolt.
Further, the engine is connected with the support frame through bolts, and the engine and the support frame are centered and fixed through the centering piece.
Further, the movable frame is an air spring supporting structure with large damping. The mode can better isolate the system from the vibration source, the system is assembled into a dynamic rigid structure, the relative stability of the interior of the system can be ensured, the probability of resonance generated under the influence of the outside can be reduced, and the stability of the system is improved.
Furthermore, the movable frame core part is of a honeycomb-shaped supporting structure. The supporting structure can fully improve the hard-to-weight ratio, and the platform with the higher hard-to-weight ratio can increase the rigidity in the system to achieve the purpose of improving the system performance.
Furthermore, the surface of the movable frame is made of ferromagnetic stainless steel, and the core part is supported by a honeycomb structure. The structure not only gives full play to the advantages of good rigidity, small temperature expansion coefficient and corrosion resistance of the ferromagnetic stainless steel material, but also improves the hard-weight ratio, increases the rigidity, reduces the deformation and improves the anti-static torque capacity; and ferromagnetic stainless steel is corrosion-resistant, can adsorb the magnetic base, and other module systems of can being convenient of putting up are applicable to and bear great, the system that has higher requirement to the vibration resistance.
Furthermore, a quality monitoring module is arranged in the movable frame, so that quality data can be fed back in real time.
In addition, the invention also provides an installation method of the thrust measurement system of the mobile micro-friction solid rocket engine, which comprises the following steps: firstly, fixing a movable frame bolt on a fixed frame; secondly, centering the force bearing pier with the movable frame through a centering piece, fixing the force bearing pier on the fixed frame through a bolt, connecting a top rod at the front end through threads, and connecting a force measuring assembly at the rear end; placing the engine on the support frame, centering the engine and the movable frame through the centering piece, fixing the engine and the movable frame through bolts, and reinforcing the engine on the support frame through the hoop; fixing a transition frame on the front skirt of the engine, wherein the transition frame is connected with the rear end of the force measuring assembly; and fifthly, fixing the fixed measuring system on the square cabin through bolts, and directly placing the square cabin on a special vehicle.
The invention has the following beneficial effects:
1. the traditional fixed test frame is upgraded to the movable micro-friction test frame, so that the function that one test frame can test the thrust of various solid rocket engines and move along with the requirement of a test field is realized.
2. The test frame has the following advantages:
(1) the kinematic pair between the movable frame and the fixed frame adopts gas lubrication, and the friction coefficient is extremely small (about 0.0005), so that the driving power can be greatly reduced;
(2) because of non-contact friction, the friction value is small and is a relatively stable value, the precision can be maintained for a long time,
(3) the air film has an error homogenization effect and can improve the motion precision of the movable frame;
(4) the thickness of the air film is hardly influenced by the speed, and the air film does not creep even at extremely low speed and moves stably;
(5) the kinematic pair between the movable frame and the fixed frame hardly generates heat, does not change viscosity, and does not need to add cooling measures;
(6) by adopting the kinematic pair between the movable frame and the fixed frame, an in-situ calibration device can be omitted, so that the whole structure is simpler and the reliability is higher.
3. According to the invention, the quality monitoring module is arranged below the movable frame, so that real-time quality parameters can be fed back.
Drawings
FIG. 1 is a prior art fixed leaf spring type solid rocket engine thrust measurement system;
FIG. 2 is a thrust measurement system of a mobile micro-friction solid rocket engine of the present application;
wherein: 1-a chassis; 2-in-situ calibration force source; 3-a bearing frame; 4-a standard force component; 5-a force transfer assembly; 6-a force measuring assembly; 7-suspension leaf springs; 8-moving the frame; 9-supporting the leaf spring; 10-an engine; 11-a portal frame; 12-fixing the frame; 13-moving the frame; 14-a support frame; 15-an engine; 16-embracing a ring; 17-a transition frame; 18-a force measuring assembly; 19-bearing pier; 20-a mandril.
Detailed Description
The invention is described in detail below by way of example with reference to the accompanying drawings.
The invention relates to a thrust measurement system of a movable micro-friction solid rocket engine, which consists of a fixed frame 12, a movable frame 13, a support frame 14, an engine 15, an embracing ring 16, a transition frame 17, a force measuring component 18, a force bearing pier 19 and a mandril 20; the movable frame 13 and the bearing pier 19 are both fixed on the fixed frame 12 through bolts, the support frame 14 is fixed on the movable frame 13 through bolts, and the hoop 16 is connected on the support frame 14; a top rod 20 is fixed at the front end of the bearing pier 19 by a bolt, and the rear end of the bearing pier is connected with a force measuring component 18; the rear end of the force measuring assembly 18 is connected with a transition frame 17, and the transition frame 17 is fixedly connected with the front skirt of the engine 15 through bolts. The device's overall structure has saved normal position calibrating device, and the structure is compared traditional fixed leaf spring connection structure simpler, and the precision is also higher.
The bearing pier 19 in the thrust measurement system of the mobile micro-friction solid rocket engine is an integral workpiece, and the inner structure of the bearing pier is provided with the consistency of the center height and the coaxiality of positioning holes; which is fixed with the movable frame 13 by a centering rear bolt through a centering piece. The bearing pier is an integral processing workpiece, so that errors generated when all parts move relatively in the prior art can be avoided, and the measurement precision is improved.
The engine 15 is connected with the support frame 14 through bolts, and the engine 15 and the support frame 14 are centered and fixed through centering pieces. The kinematic pair between the movable frame and the fixed frame hardly generates heat, viscosity change does not occur, cooling measures are not required to be added, an in-situ calibration device can be omitted by adopting the kinematic pair, and therefore the whole structure is simpler and the reliability is higher.
The movable frame 13 is an air spring support structure with large damping. The mode can better isolate the system from the vibration source, the system is assembled into a dynamic rigid structure, the relative stability of the interior of the system can be ensured, the probability of resonance generated under the influence of the outside can be reduced, and the stability of the system is improved.
The core of the movable frame 13 is a honeycomb-shaped supporting structure. The supporting structure can fully improve the hard-to-weight ratio, and the platform with the higher hard-to-weight ratio can increase the rigidity in the system to achieve the purpose of improving the system performance.
The surface of the movable frame 13 is made of ferromagnetic stainless steel, and the core part is supported by a honeycomb structure. The structure not only gives full play to the advantages of good rigidity, small temperature expansion coefficient and corrosion resistance of the ferromagnetic stainless steel material, but also improves the hard-weight ratio, increases the rigidity, reduces the deformation and improves the anti-static torque capacity; and ferromagnetic stainless steel is corrosion-resistant, can adsorb the magnetic base, and other module systems of can being convenient of putting up are applicable to and bear great, the system that has higher requirement to the vibration resistance.
The moving frame 13 is internally provided with a quality monitoring module which can feed back quality data in real time.
The installation method of the thrust measurement system of the mobile micro-friction solid rocket engine comprises the following steps: firstly, fixing a movable frame 13 on a fixed frame 12 through bolts; secondly, centering the force bearing pier 19 with the movable frame 13 through a centering piece, fixing the force bearing pier to the fixed frame 12 through a bolt, connecting a mandril 20 at the front end through threads, and connecting a force measuring assembly 18 at the rear end; thirdly, placing the engine 15 on the support frame 14, centering the engine 15 with the movable frame 13 through the centering piece, fixing the engine 15 with the movable frame 13 through bolts, and reinforcing the engine 15 on the support frame 14 through the hoop 16; fixing a transition frame 17 on the front skirt of the engine 15, and connecting the transition frame 17 with the rear end of the force measuring assembly 18; and fifthly, fixing the fixed measuring system on the square cabin through bolts, and directly placing the square cabin on a special vehicle.
The invention discloses an integral device for carrying out ground ignition test of a solid engine by placing a whole set of test system in a shelter, and the integral structure of the device omits an in-situ calibration device, so that the structure is simpler than the traditional fixed plate spring connecting structure, and the precision is higher. The square cabin is directly placed on a special vehicle, the special vehicle is used for transporting the square cabin to a test place according to test requirements, the square cabin is lifted and stably fixed on the ground, and then the engine can be installed and tested.
The above description is only an example of the present invention, and is not intended to limit the scope of the present invention. The core idea of the invention is to adopt the thrust measuring system of the mobile micro-friction solid rocket engine and the installation method thereof, and any modification, equivalent replacement, improvement and the like within the spirit and principle of the invention shall be included in the protection scope of the invention.
Claims (8)
1. The utility model provides a little frictional force solid rocket engine thrust measurement system of removal formula which characterized in that: the measuring system consists of a fixed frame (12), a movable frame (13), a support frame (14), an engine (15), an embracing ring (16), a transition frame (17), a force measuring component (18), a force bearing pier (19) and a mandril (20); the movable frame (13) and the bearing pier (19) are both fixed on the fixed frame (12) through bolts, the support frame (14) is fixed on the movable frame (13) through bolts, and the hoop (16) is connected on the support frame (14); a top rod (20) is fixed at the front end of the bearing pier (19) by a bolt, and the rear end of the bearing pier is connected with a force measuring component (18); the rear end of the force measuring component (18) is connected with a transition frame (17), and the transition frame (17) is fixedly connected with the front skirt of the engine (15) through bolts.
2. The mobile micro-friction solid rocket engine thrust measurement system of claim 1, wherein: the bearing pier (19) is an integral workpiece, and the inner structure of the bearing pier has the central height consistency and the coaxiality of positioning holes; the centering device and the movable frame (13) are fixed by a centering rear bolt through a centering piece.
3. The mobile micro-friction solid rocket engine thrust measurement system of claim 1, wherein: the engine (15) is connected with the support frame (14) through bolts, and the engine (15) and the support frame (14) are centered and fixed through centering pieces.
4. The mobile micro-friction solid rocket engine thrust measurement system of claim 1, wherein: the movable frame (13) is an air spring supporting structure with large damping.
5. The mobile micro-friction solid rocket engine thrust measurement system of claim 1, wherein: the core part of the movable frame (13) is of a honeycomb-shaped supporting structure.
6. The mobile micro-friction solid rocket engine thrust measurement system of claim 1, wherein: the surface of the movable frame (13) adopts a ferromagnetic stainless steel material, and the core part is supported by a honeycomb structure.
7. The mobile micro-friction solid rocket engine thrust measurement system of claim 1, wherein: a quality monitoring module is arranged in the movable frame (13) and can feed back quality data in real time.
8. A method of installing a thrust measurement system for a mobile micro-friction solid rocket engine according to claims 1-7, wherein installing said system comprises the steps of: firstly, fixing a movable frame 13 on a fixed frame 12 through bolts; secondly, centering the force bearing pier 19 with the movable frame 13 through a centering piece, fixing the force bearing pier to the fixed frame 12 through a bolt, connecting a mandril 20 at the front end through threads, and connecting a force measuring assembly 18 at the rear end; placing the engine 15 on the support frame 14, centering the engine 15 with the movable frame 13 through the centering piece, fixing the engine 15 with the movable frame 13 through bolts, and reinforcing the engine 15 on the support frame 14 through the hoop 16; fixing a transition frame 17 on the front skirt of the engine 15, and connecting the transition frame 17 with the rear end of the force measuring assembly 18; and fifthly, fixing the fixed measuring system on the square cabin through bolts, and directly placing the square cabin on a special vehicle.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
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| CN202010951899.0A CN112161813B (en) | 2020-09-11 | 2020-09-11 | Mobile micro-friction solid rocket engine thrust measurement system and installation method thereof |
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| CN202010951899.0A CN112161813B (en) | 2020-09-11 | 2020-09-11 | Mobile micro-friction solid rocket engine thrust measurement system and installation method thereof |
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Cited By (4)
| Publication number | Priority date | Publication date | Assignee | Title |
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| CN113686583A (en) * | 2021-10-27 | 2021-11-23 | 南通诺林金属新材料科技有限公司 | Rocket engine thrust measurement rack of high accuracy |
| CN114109656A (en) * | 2021-11-04 | 2022-03-01 | 哈尔滨工程大学 | Horizontal weak-constraint cold-flow solid rocket engine test bed and pulse triggering method |
| CN114184386A (en) * | 2021-11-29 | 2022-03-15 | 西安航天动力测控技术研究所 | Spherical solid rocket engine testing arrangement |
| CN114563192A (en) * | 2022-02-10 | 2022-05-31 | 宁波天擎航天科技有限公司 | Solid rocket engine ground test bench and temperature control method |
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| CN114184386B (en) * | 2021-11-29 | 2023-07-21 | 西安航天动力测控技术研究所 | Spherical solid rocket engine testing device |
| CN114563192A (en) * | 2022-02-10 | 2022-05-31 | 宁波天擎航天科技有限公司 | Solid rocket engine ground test bench and temperature control method |
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| CN112161813B (en) | 2023-01-31 |
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