CN108590889B - Throat bolt type variable thrust solid rocket engine ground testing device - Google Patents
Throat bolt type variable thrust solid rocket engine ground testing device Download PDFInfo
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- CN108590889B CN108590889B CN201810435205.0A CN201810435205A CN108590889B CN 108590889 B CN108590889 B CN 108590889B CN 201810435205 A CN201810435205 A CN 201810435205A CN 108590889 B CN108590889 B CN 108590889B
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- 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
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Abstract
The invention discloses a throat plug type variable thrust solid rocket engine ground test device, and belongs to the field of throat plug engine ground tests. The invention comprises a driving mechanism and a simulation mechanism; the driving mechanism comprises a motor fixing cover, a stepping motor, a sliding marker post, a motor fixing cylinder, a movement limiting nut, a first movement transfer plate, a fastening nut, a second movement transfer plate, a first throat bolt connecting rod, a pulling pressure sensor, a second throat bolt connecting rod sealing ring, a displacement sensor and a movement connecting rod; the simulation mechanism comprises a front seal head, a spring fixing piece, a left fixing cylinder, a rear seal head, a compression spring, a screw, a pressure sensor seat and a throat plug. The invention can realize the ground test of the throat bolt type variable thrust solid rocket engine and has the following advantages: (1) the test verification under different thrust and pressure intensities is realized; (2) the closed-loop control of the engine throat plug is realized; (3) the test cost is low, the obtained data is more, (4) the structure is simple, and the durability is good; (5) the driving mechanism is light in weight.
Description
Technical Field
The invention relates to a throat plug type variable thrust solid rocket engine ground test device, and belongs to the field of throat plug engine ground tests.
Background
The controllability of the solid rocket engine is poor, the solid propellant is completely stored in a combustion chamber in a charging mode, the combustion surface changes according to a preset rule after being ignited, the thrust cannot be randomly adjusted according to actual requirements in the working process, or multiple starting is realized, so that the application and development of the solid rocket engine are greatly limited, liquid rocket engines are also adopted as power devices for missile tail end correction in some weapon models, and liquid fuel engines or gas generators which are difficult to store for a long time and have small volume ratio have to be adopted in a plurality of space vehicles with limited volumes. Therefore, advanced thrust modulation technology has been one of the important directions for the development of solid rocket engines.
At present, the response time and the control precision of the variable-thrust laryngeal plug are obtained mainly by a thermal ignition test method in the test, but due to the limitations of long equipment processing period, short ignition time and material ablation, the defects of high test cost, large error, limited obtained data and the like exist, and the requirements of the variable-thrust response time and the control precision of the laryngeal plug cannot be well met in the aspects of hardware facilities, technical indexes and the like. Since the beginning of the sixties and seventies of the 20 th century, much research has been carried out abroad on the thrust control technology of solid rocket engines. Due to the limitation of calculation conditions and the like, the solid rocket engine thrust regulation technology is mainly researched in the period of time by taking experimental research as a main part, and Aerojet, Thiokol, advanced ballistic missile defense and the like are all researched in a large amount. The Aerojet is the pioneer of the research, and the solid propulsion controllable technology is firstly researched in the last 60 th century, so that the variation range of the thrust from 22250N to 1335000N is realized. These systems use medium energetic propellants and hydraulic drives, and the control systems are limited in response time and control accuracy by the use of simple computers and feedback systems. Although the thrust regulation of the engine is realized through a large number of tests in the period, certain success is achieved, but due to the reasons of sealing, weight limitation and the like, the test schemes are not really applied to the practice. With the progress of various industrial technologies such as mechanical, electronic and sealing technologies and the like and the urgent need of the thrust control technology of the solid rocket engine in the eighty-ninety years, the thrust control technology of the solid rocket engine is further widely researched and tested. However, due to the limitations of experimental means and testing techniques, the variable thrust throat plug solid rocket engine has the following problems in experimental verification: 1) the engine has single function, and the test verification under different thrusts and different pressures is difficult to realize; 2) the engine can not be reused, and the ablation of the materials of the throat plug and the nozzle is serious; 3) at present, the internal trajectory of the throttle engine is basically adjusted by adopting an open-loop control mode in China, and the closed-loop control of the throttle of the engine is required to be realized to realize the random control of the thrust of the engine; 4) the test cost is high, the obtained data is few, and the response time of the limited data to the control system is difficult to effectively verify; 5) part of the engine throat plug driving systems adopt an auxiliary hydraulic driving mode, the structure is complex, the structure is greatly simplified by adopting an electronic mechanical driving mode, and the passive quality is correspondingly reduced.
Disclosure of Invention
In order to solve the problems of single structure function, complex structure and poor durability of the existing throat bolt type variable thrust solid rocket engine ground testing device, the technical problem to be solved by the throat bolt type variable thrust solid rocket engine ground testing device disclosed by the invention is to realize the ground test of the throat bolt type variable thrust solid rocket engine, and the throat bolt type variable thrust solid rocket engine ground testing device has the following advantages: (1) the test verification under different thrust and pressure intensities is realized; (2) the closed-loop control of the engine throat plug is realized; (3) the test cost is low, the obtained data is more, (4) the structure is simple, and the durability is good; (5) the driving mechanism is light in weight.
The purpose of the invention is realized by the following technical scheme.
The invention discloses a throat-plug type variable-thrust solid rocket engine ground testing device which comprises a driving mechanism and a simulation mechanism. The driving mechanism comprises a motor fixing cover, a stepping motor, a sliding marker post, a motor fixing cylinder, a motion limiting nut, a first motion transfer plate, a fastening nut, a second motion transfer plate, a first throat bolt connecting rod, a pulling pressure sensor, a second throat bolt connecting rod, a sealing ring, a displacement sensor and a motion connecting rod. The simulation mechanism comprises a front seal head, a spring fixing piece, a left fixing cylinder, a rear seal head, a compression spring, a screw, a pressure sensor seat and a throat plug.
The connection relationship of the driving mechanism is that the stepping motor is connected and fixed on the motor fixing cover through a bolt. The step motor rotor is a threaded rod, a motion limiting nut is matched with the step motor to form a screw nut structure, the motion limiting nut rotates along with the motor rotor, translation of the motion limiting nut along the threaded rod is achieved, and therefore the second throat bolt connecting rod drives the simulation mechanism or the throat bolt to do reciprocating linear motion. The displacement sensor is installed on the sliding marker post through bolt connection, and the displacement of the simulation mechanism is measured by measuring the displacement of the first motion transmission plate. The pull pressure sensor connects the first and second laryngeal plug links. When a force acts on the tension and pressure sensor diaphragm, the resistance values of the resistance strain gauges attached to the two sides of the tension and pressure sensor are changed, converted into electric signals through corresponding circuits and input into an acquisition system, and therefore the axial stress of the simulation mechanism is measured.
The simulation mechanism has the connection relationship that the front end enclosure is of a stepped structure, a threaded hole for connecting a bolt of a motor fixing cylinder is formed in the outer cylindrical surface on one side, one side of the front end enclosure is in threaded connection with the left fixing cylinder, the step of the front end enclosure is in contact with the inner cylindrical surface of the left fixing cylinder, and a deep groove for dynamic sealing is formed in the front end enclosure. The left fixed cylinder is of a hollow cylinder structure, the two sides of the left fixed cylinder are respectively in threaded connection with the front end enclosure and the rear end enclosure, at least two pressure sensor seats are arranged according to test requirements, at least one pressure input end is used as the pressure sensor seat and used for controlling input of high-pressure cold air to simulate the gas pressure of an engine combustion chamber, the left fixed cylinder further comprises at least one pressure sensor seat used for installing a pressure sensor, and the pressure sensor is used for measuring the pressure in the simulation mechanism. The second laryngeal plug link connects either the compression spring or the experimental size of the laryngeal plug depending on the purpose of the experiment. When a cold gas test was performed to study the load characteristics of the test size laryngeal plugs, the laryngeal plug connector rods connected the test size laryngeal plugs. When the simulation mechanism is used for analyzing the response time and the control precision of the driving mechanism under the load, the second throat bolt connecting rod is connected with the compression spring. The elastic force provided by the compression spring is used for simulating the axial stress in the movement process of the laryngeal plug, and the axial stress of the simulation mechanism is measured by a pulling pressure sensor arranged between the first laryngeal plug connecting rod and the second laryngeal plug connecting rod so as to analyze the response time and the control precision of the driving mechanism under the load. The center of the spring fixing piece is provided with a threaded hole for the bolt connection of the second throat bolt connecting rod, and the spring fixing piece is provided with a deep groove for providing space for the movement of the compression spring. The spring selected by the simulation mechanism is a compression spring, and the compression spring is sleeved in an annular groove of the rear seal head and the spring fixing piece for effectively avoiding self bending deformation or breakage failure caused by overlarge stress or uneven stress of the compression spring in the motion process of the second throat plug connecting rod. In addition, the front seal head and the rear seal head are respectively fixed with the left fixed cylinder, and the spring fixing piece is fixed with the second throat bolt connecting rod through a screw rod.
Preferably, one side of the motor fixing cover is provided with a boss, so that the motor fixing cover is convenient to disassemble and assemble; threaded holes are uniformly distributed in the circumferential direction of the motor fixing cover, and the motor fixing cover is connected and fixed with the stepping motor through bolts; the outer cylindrical surface of the motor fixing cover is of a stepped structure, so that the motor fixing cylinder is convenient to accept.
Preferably, one side of the sliding marker post is of a threaded structure, and threaded holes for mounting a clamp and fixing the displacement sensor are uniformly distributed in the other side of the sliding marker post.
Preferably, the motor fixing cylinder is a cylindrical shell, a circumferential groove for dismounting and mounting is milled in the wall surface, and two sides of the motor fixing cylinder are respectively connected with the motor fixing cover and the front end socket through bolts.
Preferably, the first motion transfer plate is of a circular plate-shaped structure, circular through holes are uniformly distributed in the center and the circumferential direction, and arc-shaped wall surfaces on the periphery are symmetrically distributed, so that the first motion transfer plate is convenient to detach and mount.
Preferably, both ends of the second throat bolt connecting rod are provided with threaded holes, and the outer cylindrical surface is uniformly provided with deep grooves for shaft dynamic sealing.
The invention discloses a working method of a throat-plug type variable-thrust solid rocket engine ground testing device, which comprises the following steps of:
the method comprises the following steps: determining the gas pressure of the left fixed cylinder, the throat plug displacement regulating quantity and the control precision according to the test purpose;
step two: selecting a displacement sensor and a pull pressure sensor which meet the measuring range of the test purpose;
step three: assembling a ground testing device according to the connection relation of the throat bolt type variable thrust solid rocket engine ground testing device;
step four: checking the rationality and the assembly stability of the throat bolt type variable thrust solid rocket engine ground testing device;
step five: high-pressure gas is introduced into the pressure sensor seat, and the stepping motor is used for driving the second throat bolt connecting rod to reciprocate so as to check the air tightness of the device;
step six: if the throat-bolt-type variable-thrust solid rocket engine ground testing device leaks air, repeating the fifth step until the ground testing device meets the expected requirements;
step seven: selecting and executing the step eight or the step nine according to the test purpose, and carrying out a corresponding ground test;
step eight: and when the simulation mechanism carries out cold gas test to research the load characteristics of the laryngeal plug with the experimental size, the second laryngeal plug connecting rod is connected with the laryngeal plug with the experimental size. The reciprocating motion of the laryngeal suppository connecting rod is pushed through the stepping motor, the displacement adjustment of the laryngeal suppository is achieved, and the laryngeal suppository load data of the experiment size is acquired through the pulling pressure sensor. The pressure of input cold air is changed in the test, and the research on the load characteristics of the laryngeal plug under different pressures is realized.
Step nine: when the simulation mechanism is used for analyzing the response time and the control precision of the driving mechanism under the load, the second throat bolt connecting rod is connected with the compression spring. The elastic force provided by the compression spring is used for simulating the axial stress of the second throat bolt connecting rod in the motion process, the axial stress of the simulation mechanism is measured by a pulling pressure sensor arranged between the first throat bolt connecting rod and the second throat bolt connecting rod, and is transmitted to a driving mechanism control system through real-time feedback so as to analyze the response time and the control precision of the driving mechanism with load under closed-loop control. In the test, the test verification of the response time and the control precision of the driving mechanism with load under different thrusts is realized by changing the rigidity of the compression spring.
Advantageous effects
1. When cold air tests are carried out to research the load characteristics of the throats with the experimental size, the second throats are connected with the throats with the experimental size through connecting rods; the reciprocating motion of the first laryngeal plug connecting rod is pushed by the stepping motor, so that the displacement adjustment of the laryngeal plug is realized, and the load data of the laryngeal plug with the experimental size is acquired by pulling the pressure sensor; the pressure of input cold air is changed in the test, and the research on the load characteristics of the laryngeal plug under different pressures is realized.
2. When the throat bolt type variable thrust solid rocket engine ground testing device is used for analyzing the response time and the control precision of a driving mechanism, a second throat bolt connecting rod is connected with a compression spring; the elastic force provided by the compression spring is used for simulating the axial stress in the movement process of the laryngeal plug, the axial stress of the simulation mechanism is measured by a pull pressure sensor arranged between the first laryngeal plug connecting rod and the second laryngeal plug connecting rod, and is transmitted to the driving mechanism control system through real-time feedback so as to be used for analyzing the response time and the control precision of the driving mechanism under closed-loop control; in the test, the test verification of the response time and the control precision of the driving mechanism with load under different thrusts is realized by changing the rigidity of the compression spring.
3. Compared with a throat plug and a nozzle material under a heat flow test condition, the throat plug type variable thrust solid rocket engine ground testing device disclosed by the invention has the advantages that the ablation is serious, the throat plug deformation is small under a cold air test condition, the material is not ablated, the repeated use is realized, and the material durability is high.
4. Compared with the ground testing device of the throat-plug type variable-thrust solid rocket engine, the ground testing device has the advantages that the ignition cost is high, the testing conditions are limited by the field, and the test verification of a large number of repeatability is difficult to perform; the cold air test has low test cost, is not limited by site environment, is convenient for multiple times of test verification, obtains more data, and a large amount of data has deeper understanding on the research of the response time of the control system and the load characteristic of the laryngeal plug.
5. Compared with a part of engine throat plug driving systems adopting an auxiliary hydraulic driving mode, the throat plug type variable thrust solid rocket engine ground testing device disclosed by the invention can simplify the structure and reduce the corresponding passive mass by adopting an electronic mechanical driving mode.
Drawings
FIG. 1 is a schematic view of a throat bolt type thrust variable solid rocket engine ground test device (simulation mechanism for cold gas test and research experiment size throat bolt load characteristics)
FIG. 2 is a schematic structural diagram of a throat bolt type variable thrust solid rocket engine ground test device (simulation mechanism for verifying response time and control accuracy of a driving mechanism under load)
Wherein: 1-driving mechanism, 2-simulation mechanism, 1.1-motor fixing cover, 1.2-stepping motor, 1.3-sliding marker post, 1.4-motor fixing cylinder, 1.5-motion limiting nut, 1.6-first motion transmission plate, 1.7-fastening nut, 1.8-second motion transmission plate, 1.9-first throat bolt connecting rod, 1.10-pulling pressure sensor, 1.11-second throat bolt connecting rod, 1.12-sealing ring, 1.13-displacement sensor, 1.14-motion connecting rod, 2.1-front sealing head, 2.2-spring fixing piece, 2.3-left fixing cylinder, 2.4-rear sealing head, 2.5-compression spring, 2.6-screw rod, 2.7-pressure sensor seat and 2.8-throat bolt.
Detailed Description
For a better understanding of the objects and advantages of the present invention, reference should be made to the following detailed description taken in conjunction with the accompanying drawings and examples.
Example 1:
the ground testing device for the throat-plug type variable-thrust solid rocket engine disclosed by the embodiment comprises a driving mechanism 1 and a simulation mechanism 2. The driving mechanism 1 comprises a motor fixing cover 1.1, a stepping motor 1.2(87000 series linear driver), a sliding mark post 1.3, a motor fixing cylinder 1.4, a motion limiting nut 1.5, a first motion transmission plate 1.6, a fastening nut 1.7(M8), a second motion transmission plate 1.8, a first throat bolt connecting rod 1.9, a pulling pressure sensor 1.10(20kg), a second throat bolt connecting rod 1.11, a sealing ring 1.12, a displacement sensor 1.13(10mm) and a motion connecting rod 1.14. The simulation mechanism 2 comprises a front end enclosure 2.1, a spring fixing piece 2.2, a left fixing cylinder 2.3, a rear end enclosure 2.4, a compression spring 2.5, a screw rod 2.6, a pressure sensor seat 2.7(M20 multiplied by 1.5) and a throat plug 2.8.
The connection relationship of the driving mechanism 1 is that a stepping motor 1.2 is fixed on a motor fixing cover 1.1 through bolt connection. The rotor of the stepping motor 1.2 is a threaded rod, a motion limiting nut 1.5 is matched with the stepping motor 1.2 to form a screw nut structure, the motion limiting nut 1.5 rotates along with the motor rotor, translation of the motion limiting nut 1.5 along the threaded rod is achieved, and therefore the second throat bolt connecting rod 1.11 drives the simulation mechanism 2 or the throat bolt 2.8 to do reciprocating linear motion. The displacement sensor 1.13 is installed on the sliding marker post 1.3 through bolt connection, and the displacement of the simulation mechanism 2 is measured by measuring the displacement of the first motion transfer plate 1.6. The pull pressure sensor 1.10 connects the first 1.9 and second 1.11 throat bolt. When a force acts on the tension and pressure sensor diaphragm, the resistance values of the resistance strain gauges attached to the two sides of the tension and pressure sensor are changed, converted into electric signals through corresponding circuits and input into an acquisition system, and therefore the axial stress of the simulation mechanism 2 is measured.
The connection relation of the simulation mechanism 2 is that the front end enclosure 2.1 is of a stepped structure, a threaded hole for connecting a bolt 1.4 of a motor fixing cylinder is formed in the outer cylindrical surface of one side, one side of the front end enclosure is in threaded connection with a left fixing cylinder 2.3, the step of the front end enclosure 2.1 is in contact with the inner cylindrical surface of the left fixing cylinder 2.3, and a deep groove for dynamic sealing is formed in the front end enclosure 2.1. The left fixed cylinder 2.3 is of a hollow cylinder structure, two sides of the left fixed cylinder are respectively in threaded connection with the front seal head 2.1 and the rear seal head 2.4, at least two pressure sensor bases 2.7 are arranged according to test requirements, at least one pressure input end is used as the pressure sensor base 2.7 and used for controlling input high-pressure cold air to simulate the gas pressure of an engine combustion chamber, and the left fixed cylinder also at least comprises the pressure sensor base 2.7 used for installing a pressure sensor, and the pressure sensor is used for measuring the pressure in the simulation mechanism 2. The second throat bar 1.11 is attached to either a compression spring 2.5 or a pilot sized throat 2.8 depending on the purpose of the test. When a cold gas test is performed to study the load characteristics of the experimental size of the throat plug 2.8, a second throat plug connecting rod 1.11 connects the experimental size of the throat plug 2.8. The simulation mechanism 2 is used for analyzing the response time and control accuracy of the driving mechanism 1 under load, and the second throat bolt connecting rod 1.11 is connected with a compression spring 2.5. The elastic force provided by the compression spring 2.5 is used for simulating the axial stress in the movement process of the laryngeal plug, and the axial stress of the simulation mechanism 2 is measured by a pull pressure sensor 1.10 arranged between the first laryngeal plug connecting rod 1.9 and the second laryngeal plug connecting rod 1.11 so as to be used for analyzing the response time and the control precision of the driving mechanism 1 under the load. The spring holder 2.2 is centrally provided with a threaded hole for the screw connection of the second throat bolt 1.11 and with a deep groove for providing space for the movement of the compression spring 2.5. The spring selected by the simulation mechanism 2 is a compression spring 2.5, and in order to effectively avoid the bending deformation or breakage failure of the compression spring 2.5 caused by overlarge stress or uneven stress in the movement process of the second throat bolt connecting rod 1.11, the compression spring 2.5 is sleeved in the annular groove of the rear end enclosure and the spring fixing piece 2.2. In addition, the front end enclosure 2.1 and the rear end enclosure 2.4 are respectively fixed with the left fixed cylinder 2.3, and the spring fixing piece 2.2 is fixed with the second throat bolt connecting rod 1.11 through a screw rod 2.6.
A boss is arranged on one side of the motor fixing cover 1.1, so that the motor fixing cover is convenient to disassemble and assemble; threaded holes are uniformly distributed in the circumferential direction of the motor fixing cover 1.1, and the stepping motor 1.2 is connected and fixed through bolts; the outer cylindrical surface of the motor fixing cover 1.1 is of a stepped structure, so that the motor fixing cylinder 1.4 can be conveniently accepted.
One side of the sliding marker post 1.3 is of a threaded structure, and threaded holes for mounting a clamp and fixing the displacement sensor 1.13 are uniformly distributed in the other side of the sliding marker post.
The motor fixing cylinder 1.4 is a cylindrical shell, a circumferential groove for dismounting and mounting is milled in the wall surface, and two sides of the motor fixing cylinder are respectively connected with the motor fixing cover 1.1 and the front end enclosure 2.1 through bolts.
The first motion transfer plate 1.6 is of a circular plate-shaped structure, circular through holes are uniformly distributed in the center and the circumferential direction, and arc-shaped wall surfaces on the periphery are symmetrically distributed, so that the first motion transfer plate is convenient to detach and install.
Threaded holes are formed in two ends of the second throat bolt connecting rod 1.11, and deep grooves are uniformly formed in the outer cylindrical surface and used for shaft dynamic sealing.
The working method of the throat-plug type variable-thrust solid rocket engine ground testing device disclosed by the embodiment comprises the following steps of:
the method comprises the following steps: according to the test purpose, 2.3 gas pressure of a left fixing cylinder of 10Mpa, 2.8 displacement regulating quantity of a throat plug of 5mm and 0.2kg control precision are determined;
step two: selecting a 10mm displacement sensor 1.13 and a 20kg pull pressure sensor 1.10 which meet the test purpose;
step three: assembling a ground testing device according to the connection relation of the throat bolt type variable thrust solid rocket engine ground testing device;
step four: checking the rationality and the assembly stability of the throat bolt type variable thrust solid rocket engine ground testing device;
step five: by connecting 5Mpa high-pressure gas to the pressure sensor seat 2.7 and using the stepping motor 1.2 to drive the second throat bolt connecting rod 1.11 to reciprocate, the air tightness of the threaded connection in the simulation mechanism 2 and the dynamic seal between the second throat bolt connecting rod 1.11 and the front end enclosure 2.1 is checked;
step six: if the throat-bolt-type variable-thrust solid rocket engine ground testing device leaks air, repeating the fifth step until the ground testing device meets the expected requirements;
step seven: selecting and executing the step eight or the step nine according to the test purpose, and carrying out a corresponding ground test;
step eight: simulation mechanism 2 when conducting a cold gas test to study the load characteristics of an experimentally sized throat plug 2.8, a second throat plug connecting rod 1.11 is connected to the throat plug 2.8. Two pressure sensor bases 2.7 are arranged on the left fixed cylinder 2.3, one pressure input end is used as the pressure sensor base 2.7 and is used for controlling and inputting 10Mpa high-pressure cold air to simulate the gas pressure of an engine combustion chamber, the other pressure sensor base 2.7 is provided with a 20Mpa range pressure sensor, and the 20Mpa range pressure sensor is used for measuring the pressure in the simulation mechanism 2. The reciprocating motion of the first throat plug connecting rod 1.9 is pushed through the stepping motor 1.2, so that the displacement adjustment of the throat plug 2.8 with the total length of 90.2mm is realized, and the load data of the throat plug 2.8 is acquired through the pull pressure sensor 1.10. In the test, the pressure of input cold air is changed to 5Mpa, 10Mpa and 15Mpa, so that the research on the 2.8 load characteristic of the laryngeal plug under different pressures is realized.
Step nine: the simulation mechanism 2 is used for analyzing the response time and control accuracy of the driving mechanism 1 under load, and the second throat bolt connecting rod 1.11 is connected with a compression spring 2.5. The elastic force provided by the compression spring 2.5 is used for simulating the axial stress of the second throat bolt connecting rod 1.11 in the motion process, the axial stress of the simulation mechanism 2 is measured by a pull pressure sensor 1.10 which is arranged in the middle of the first throat bolt connecting rod 1.9 and the second throat bolt connecting rod 1.11 and has the range of 20kg, and the axial stress is transmitted to a control system of the driving mechanism 1 through real-time feedback so as to be used for analyzing the response time and the control precision of the driving mechanism 1 under the condition of closed-loop control under the load. In the test, the rigidity of the compression spring 2.5 is changed, so that the test verification of the response time and the control precision of the drive mechanism 1 with loads of 5kg, 10kg and 15kg is realized.
The above detailed description is intended to illustrate the objects, aspects and advantages of the present invention, and it should be understood that the above detailed description is only exemplary of the present invention and is not intended to limit the scope of the present invention, and any modifications, equivalents, improvements and the like made within the spirit and principle of the present invention should be included in the scope of the present invention.
Claims (7)
1. The utility model provides a throat bolt formula variable thrust solid rocket engine ground testing arrangement which characterized in that: comprises a driving mechanism (1) and a simulation mechanism (2); the driving mechanism (1) comprises a motor fixing cover (1.1), a stepping motor (1.2), a sliding marker post (1.3), a motor fixing cylinder (1.4), a motion limiting nut (1.5), a first motion transfer plate (1.6), a fastening nut (1.7), a second motion transfer plate (1.8), a first throat plug connecting rod (1.9), a pull pressure sensor (1.10), a second throat plug connecting rod (1.11), a sealing ring (1.12), a displacement sensor (1.13) and a motion connecting rod (1.14); the simulation mechanism (2) comprises a front seal head (2.1), a spring fixing piece (2.2), a left fixing cylinder (2.3), a rear seal head (2.4), a compression spring (2.5), a screw (2.6), a pressure sensor seat (2.7) and a throat plug (2.8);
the connection relation of the driving mechanism (1) is that a stepping motor (1.2) is connected and fixed on a motor fixing cover (1.1) through a bolt; the rotor of the stepping motor (1.2) is a threaded rod, a motion limiting nut (1.5) is matched with the stepping motor (1.2) to form a screw nut structure, the motion limiting nut (1.5) rotates along with the rotor of the motor, translation of the motion limiting nut (1.5) along the threaded rod is realized, and the second throat bolt connecting rod (1.11) drives the simulation mechanism (2) or the throat bolt (2.8) to do reciprocating linear motion; the displacement sensor (1.13) is connected and installed on the sliding marker post (1.3) through a bolt, and the displacement of the simulation mechanism (2) is measured by measuring the displacement of the first motion transfer plate (1.6); the pulling pressure sensor (1.10) connects the first laryngeal plug connecting rod (1.9) and the second laryngeal plug connecting rod (1.11); when a force acts on the diaphragm of the tension and pressure sensor (1.10), the resistance values of the resistance strain gauges attached to the two sides of the tension and pressure sensor (1.10) are changed, converted into electric signals through corresponding circuits and input into an acquisition system, so that the axial stress of the simulation mechanism (2) is measured;
the connection relation of the simulation mechanism (2) is that the front seal head (2.1) is of a ladder structure, a threaded hole for connecting a bolt with a motor fixing cylinder (1.4) is formed in the outer cylindrical surface on one side, the left fixing cylinder (2.3) is in threaded connection with one side, the step of the front seal head (2.1) is in contact with the inner cylindrical surface of the left fixing cylinder (2.3), and a deep groove for dynamic sealing is formed in the front seal head (2.1); the left fixed cylinder (2.3) is of a hollow cylinder structure, two sides of the left fixed cylinder are respectively in threaded connection with the front seal head (2.1) and the rear seal head (2.4), and at least two pressure sensor seats (2.7) are arranged according to test requirements, wherein at least one pressure input end is used as the pressure sensor seat (2.7) for controlling input high-pressure cold air to simulate the gas pressure of an engine combustion chamber, and the left fixed cylinder also at least comprises the pressure sensor seat (2.7) for installing a pressure sensor, and the pressure sensor is used for measuring the pressure in the simulation mechanism; the second laryngeal plug connecting rod (1.11) is connected with a compression spring (2.5) or a laryngeal plug (2.8) with an experimental size according to the experimental purpose; when cold gas tests are performed to study the load characteristics of the experimental size of the laryngeal plug (2.8), the laryngeal plug connecting rod is connected to the experimental size of the laryngeal plug (3); when the simulation mechanism (2) is used for analyzing the response time and the control precision of the driving mechanism (1) under load, the second throat plug connecting rod (1.11) is connected with the compression spring (2.5); the elastic force provided by the compression spring (2.5) is used for simulating the axial stress of the laryngeal plug (2.8) in the motion process, and the axial stress of the simulation mechanism (2) is measured by a pull pressure sensor (1.10) arranged between the first laryngeal plug connecting rod (1.9) and the second laryngeal plug connecting rod (1.11) so as to be used for analyzing the response time and the control precision of the driving mechanism (1) under the load; the center of the spring fixing piece (2.2) is provided with a threaded hole for the bolt connection of the second throat bolt connecting rod (1.11), and the spring fixing piece is provided with a deep groove for providing a space for the movement of the compression spring (2.5); the spring selected by the simulation mechanism (2) is a compression spring (2.5), in order to effectively avoid self bending deformation or breakage failure caused by overlarge stress or uneven stress of the compression spring (2.5) in the movement process of the second throat plug connecting rod (1.11), the compression spring (2.5) is sleeved in the annular groove of the rear end enclosure (2.4) and the spring fixing piece (2.2); in addition, the front seal head (2.1) and the rear seal head (2.4) are respectively fixed with the left fixed cylinder (2.3), and the spring fixing piece (2.2) is fixed with the second throat plug connecting rod (1.11) through a screw (2.6).
2. The throat-plug type variable thrust solid rocket engine ground test device according to claim 1, wherein: a boss is arranged on one side of the motor fixing cover (1.1) so as to be convenient to detach and install; threaded holes are uniformly distributed in the circumferential direction of the motor fixing cover (1.1), and the stepping motor (1.2) is connected and fixed through bolts; the outer cylindrical surface of the motor fixing cover (1.1) is of a stepped structure, so that the motor fixing cylinder (1.4) can be conveniently accepted.
3. The throat-plug type variable thrust solid rocket engine ground test device according to claim 1, wherein: one side of the sliding marker post (1.3) is of a threaded structure, and threaded holes for mounting a clamp and fixing the displacement sensor (1.13) are uniformly distributed on the other side of the sliding marker post.
4. The throat-plug type variable thrust solid rocket engine ground test device according to claim 1, wherein: the motor fixing cylinder (1.4) is a cylindrical shell, a circumferential groove for dismounting and mounting is milled in the wall surface, and two sides of the motor fixing cylinder are respectively connected with the motor fixing cover (1.1) and the front seal head (2.1) through bolts.
5. The throat-plug type variable thrust solid rocket engine ground test device according to claim 1, wherein: the first motion transfer plate (1.6) is of a circular plate-shaped structure, circular through holes are uniformly distributed in the center and the circumferential direction, and arc-shaped wall surfaces on the periphery are symmetrically distributed, so that the first motion transfer plate is convenient to detach and install.
6. The throat-plug type variable thrust solid rocket engine ground test device according to claim 1, wherein: both ends of the second throat plug connecting rod (1.11) are provided with threaded holes, and the outer cylindrical surface is uniformly provided with deep grooves for shaft dynamic sealing.
7. A throat-plug variable thrust solid rocket engine ground test device according to claim 1, 2, 3, 4, 5 or 6, wherein: the working method comprises the following steps:
the method comprises the following steps: determining the gas pressure of the left fixed cylinder (2.3), the displacement regulating quantity of the laryngeal plug (2.8) and the control precision according to the test purpose;
step two: selecting a displacement sensor (1.13) and a pull pressure sensor (1.10) which meet the measuring range of the test purpose;
step three: assembling a ground testing device according to the connection relation of the throat bolt type variable thrust solid rocket engine ground testing device;
step four: checking the rationality and the assembly stability of the throat bolt type variable thrust solid rocket engine ground testing device;
step five: high-pressure gas is introduced into the pressure sensor seat (2.7), and the stepping motor (1.2) is used for driving the second laryngeal plug connecting rod (1.11) to reciprocate, so that the air tightness of the device is checked;
step six: if the throat-bolt-type variable-thrust solid rocket engine ground testing device leaks air, repeating the fifth step until the ground testing device meets the expected requirements;
step seven: selecting and executing the step eight or the step nine according to the test purpose, and carrying out a corresponding ground test;
step eight: when the simulation mechanism (2) is used for researching the load characteristics of the laryngeal plug (2.8) with the experimental size through a cold gas test, the second laryngeal plug connecting rod (1.11) is connected with the laryngeal plug (2.8) with the experimental size; the reciprocating motion of the laryngeal plug connecting rod is pushed by the stepping motor (1.2), so that the displacement adjustment of the laryngeal plug (2.8) is realized, and the load data of the laryngeal plug (2.8) with the experimental size is acquired by pulling the pressure sensor (1.10); the pressure of input cold air is changed in the test, so that the research on the load characteristic of the laryngeal plug (2.8) under different pressures is realized;
step nine: when the simulation mechanism (2) is used for analyzing the response time and the control precision of the driving mechanism (1) under load, the second throat plug connecting rod (1.11) is connected with the compression spring (2.5); the elastic force provided by the compression spring (2.5) is used for simulating the axial stress of the second larynx bolt connecting rod (1.11) in the motion process, the axial stress of the simulation mechanism (2) is measured by a pull pressure sensor (1.10) arranged between the first larynx bolt connecting rod (1.9) and the second larynx bolt connecting rod (1.11), and is transmitted to a control system of the driving mechanism (1) through real-time feedback so as to be used for analyzing the response time and the control precision of the driving mechanism (1) with load under closed-loop control; in the test, the rigidity of the compression spring (2.5) is changed, so that the response time of the driving mechanism (1) with load under different thrusts and the test verification of the control precision are realized.
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| CN109556842A (en) * | 2018-10-31 | 2019-04-02 | 北京动力机械研究所 | A kind of adjustable load on spring simulator of load |
| CN109632171B (en) * | 2019-01-08 | 2024-05-24 | 陕西航天西诺美灵电气有限公司 | Rocket engine micro-force measuring device |
| CN110109374B (en) * | 2019-05-13 | 2022-09-20 | 九州云箭(北京)空间科技有限公司 | Semi-physical simulation method and device for thrust adjusting system of liquid rocket engine |
| CN110344966B (en) * | 2019-07-16 | 2021-01-05 | 北京强度环境研究所 | Device and method for constructing free boundary of solid rocket ground test |
| CN111766073B (en) * | 2020-07-09 | 2021-08-03 | 北京理工大学 | Solid rocket engine high-speed spin test holding device |
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| CN113255145B (en) * | 2021-06-03 | 2021-09-24 | 中国人民解放军国防科技大学 | Attitude and orbit control engine throat plug motion time sequence experimental design method, device and equipment |
| CN113638823B (en) * | 2021-08-10 | 2022-06-17 | 北京理工大学 | Needle valve type flow-adjustable gas generator ground test device |
| CN113933044A (en) * | 2021-12-09 | 2022-01-14 | 星河动力(北京)空间科技有限公司 | Test method, device and platform for flexible joint assembly of rocket engine spray pipe |
| CN115726902B (en) * | 2022-11-21 | 2024-05-14 | 北京中科宇航技术有限公司 | Solid rocket engine working for long time and throat bolt device thereof |
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| CN203689142U (en) * | 2013-12-10 | 2014-07-02 | 上海新力动力设备研究所 | Aerodynamic force simulating loading device for pintle engine servo system |
| JP6919897B2 (en) * | 2015-05-29 | 2021-08-18 | ノストラム エナジー ピーティーイー．リミテッドＮｏｓｔｒｕｍ Ｅｎｅｒｇｙ Ｐｔｅ．Ｌｔｄ． | Orifice plate of jet collision type fluid injector |
| CN205785819U (en) * | 2016-05-24 | 2016-12-07 | 华中科技大学 | A kind of test device for rocket engine ground firing |
| CN106930866B (en) * | 2017-01-26 | 2018-10-30 | 北京航空航天大学 | A kind of solid-liquid rocket ground experiment jet pipe blocking cover structure |
| CN107023420B (en) * | 2017-05-16 | 2018-09-21 | 北京理工大学 | A kind of Secondary Flow larynx bolt rocket engine with thrust controllable function |
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