CN114563192A - Solid rocket engine ground test bench and temperature control method - Google Patents
Solid rocket engine ground test bench and temperature control method Download PDFInfo
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- CN114563192A CN114563192A CN202210123964.XA CN202210123964A CN114563192A CN 114563192 A CN114563192 A CN 114563192A CN 202210123964 A CN202210123964 A CN 202210123964A CN 114563192 A CN114563192 A CN 114563192A
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- 238000012360 testing method Methods 0.000 title claims abstract description 73
- 239000007787 solid Substances 0.000 title claims abstract description 24
- 238000000034 method Methods 0.000 title claims abstract description 12
- 238000004321 preservation Methods 0.000 claims abstract description 56
- 238000010438 heat treatment Methods 0.000 claims abstract description 47
- 238000009413 insulation Methods 0.000 claims abstract description 35
- 238000001816 cooling Methods 0.000 claims abstract description 34
- 239000010410 layer Substances 0.000 claims description 34
- IJGRMHOSHXDMSA-UHFFFAOYSA-N Atomic nitrogen Chemical compound N#N IJGRMHOSHXDMSA-UHFFFAOYSA-N 0.000 claims description 22
- 239000007788 liquid Substances 0.000 claims description 21
- 229910052757 nitrogen Inorganic materials 0.000 claims description 11
- 230000017525 heat dissipation Effects 0.000 claims description 9
- 239000011229 interlayer Substances 0.000 claims description 9
- 230000005540 biological transmission Effects 0.000 claims description 7
- 238000006073 displacement reaction Methods 0.000 claims description 3
- 238000002360 preparation method Methods 0.000 description 4
- 239000007921 spray Substances 0.000 description 4
- 238000005485 electric heating Methods 0.000 description 2
- 238000005516 engineering process Methods 0.000 description 2
- 238000005057 refrigeration Methods 0.000 description 2
- 238000013459 approach Methods 0.000 description 1
- 230000009286 beneficial effect Effects 0.000 description 1
- 239000000110 cooling liquid Substances 0.000 description 1
- LYCAIKOWRPUZTN-UHFFFAOYSA-N ethylene glycol Natural products OCCO LYCAIKOWRPUZTN-UHFFFAOYSA-N 0.000 description 1
- 125000003827 glycol group Chemical group 0.000 description 1
- WGCNASOHLSPBMP-UHFFFAOYSA-N hydroxyacetaldehyde Natural products OCC=O WGCNASOHLSPBMP-UHFFFAOYSA-N 0.000 description 1
- 210000001503 joint Anatomy 0.000 description 1
- 238000005259 measurement Methods 0.000 description 1
- 238000005457 optimization Methods 0.000 description 1
- 238000012546 transfer Methods 0.000 description 1
- 238000012795 verification Methods 0.000 description 1
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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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- B—PERFORMING OPERATIONS; TRANSPORTING
- B65—CONVEYING; PACKING; STORING; HANDLING THIN OR FILAMENTARY MATERIAL
- B65D—CONTAINERS FOR STORAGE OR TRANSPORT OF ARTICLES OR MATERIALS, e.g. BAGS, BARRELS, BOTTLES, BOXES, CANS, CARTONS, CRATES, DRUMS, JARS, TANKS, HOPPERS, FORWARDING CONTAINERS; ACCESSORIES, CLOSURES, OR FITTINGS THEREFOR; PACKAGING ELEMENTS; PACKAGES
- B65D81/00—Containers, packaging elements, or packages, for contents presenting particular transport or storage problems, or adapted to be used for non-packaging purposes after removal of contents
- B65D81/18—Containers, packaging elements, or packages, for contents presenting particular transport or storage problems, or adapted to be used for non-packaging purposes after removal of contents providing specific environment for contents, e.g. temperature above or below ambient
-
- 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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- G—PHYSICS
- G01—MEASURING; TESTING
- G01M—TESTING STATIC OR DYNAMIC BALANCE OF MACHINES OR STRUCTURES; TESTING OF STRUCTURES OR APPARATUS, NOT OTHERWISE PROVIDED FOR
- G01M99/00—Subject matter not provided for in other groups of this subclass
- G01M99/002—Thermal testing
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- Testing Of Engines (AREA)
Abstract
The invention discloses a solid rocket engine ground test bench and a temperature control method, and relates to the technical field of engine tests; the method comprises the following steps: the outer wall of one side of the heat preservation box body is provided with a heating and refrigerating system, one end of the heating and refrigerating system is provided with a first three-way valve, the other end of the heating and refrigerating system is provided with a second three-way valve, the first three-way valve is connected with one end of a cooling pipe, the cooling pipe penetrates through one side of the heat preservation box body and is arranged in the inner wall of the heat preservation box body in a surrounding mode to form a coil pipe, and the other end of the cooling pipe is connected with the second three-way valve; circulating media and a test rack are arranged in the cooling pipe in a flowing manner; the test stand is arranged in the insulation can body and comprises a test stand base, an engine support and a thrust support, the engine support and the thrust support are both arranged on the test stand base, and the output end of the thrust support is connected with the engine support; when the system is used, the control acquisition system of the heat preservation cabin and the control acquisition system of the engine test bed can be integrated into one system.
Description
Technical Field
The invention relates to the technical field of engine tests, in particular to a solid rocket engine ground test bench and a temperature control method.
Background
The engine test and test technology of the solid rocket engine (aerospace) is an important component of the solid propulsion technology, and before the aerospace engine is subjected to test flight, a test-and-reach verification test needs to be carried out on the ground. As engines become more mature, the applications of the engines become more widespread.
The use environment of the solid rocket engine includes four seasons environment including spring, summer, autumn and winter, and also includes various environments such as ground, high altitude, plateau and the like, so that the engine does not only work in a normal temperature environment, but also often works in a high temperature or low temperature environment, so that the high temperature or low temperature storage is carried out in the engine ground test, and the engine ground ignition test can be carried out after the temperature reaches the specified temperature.
The engine is first kept warm in a heat-insulating box (high or low temperature box), and when the temperature in the heat-insulating box (or the surface temperature of the engine) reaches a set temperature, the engine is kept warm for a time t1(t1 is a time specified by the standard, the same applies below). After time t1, the engine was taken out of the high and low temperature boxes, and then transported to an engine test stand to prepare for a ground ignition test. Over time, the temperature of the engine itself will gradually approach the ambient temperature at the time of commissioning rather than the temperature required by the engine, and a series of pre-ignition preparations will be carried out after the engine is delivered to the test stand. Thus, the engine temperature varies, and the preparation of the engine at a high or low temperature causes a series of troubles (poor operation).
Disclosure of Invention
The invention aims to provide a solid rocket engine ground test bench and a temperature control method, which are used for solving the technical problems.
A solid rocket engine ground test rig, comprising: the heating and refrigerating system is arranged on the outer wall of one side of the heat preservation box body, a first three-way valve is arranged at one end of the heating and refrigerating system, a second three-way valve is arranged at the other end of the heating and refrigerating system, the first three-way valve is connected with one end of a cooling pipe, the cooling pipe penetrates through one side of the heat preservation box body and is arranged in the inner wall of the heat preservation box body in a surrounding mode to form a coil pipe, and the other end of the cooling pipe is connected with the second three-way valve; a circulating medium flows in the cooling pipe,
one side of the heat preservation box body is movably connected with the cover body; the inner walls of the heat preservation box body and the cover body are both provided with a heat preservation layer;
a test frame; the test rack is arranged in the heat-insulation box body and comprises a test rack base, an engine support and a thrust support, the engine support and the thrust support are both arranged on the test rack base, the output end of the thrust support is connected with the engine support, a baffle is arranged on the thrust support, and a thrust sensor is arranged on the baffle;
An engine; the engine is mounted on the engine mount.
As further preferred, the insulation box body is divided into an outer layer, an interlayer and an inner layer from outside to inside, the inner layer is an insulation layer, the interlayer consists of vacuum interlayers, and the outer layer consists of insulation boards and encloses the box body to form an inner cavity capable of containing the engine.
As a further preference, the thrust support comprises a support box body, a worm wheel, a worm, a motor, a screw nut, a radial thrust ball bearing and a screw, the support box body is installed on the base of the test bed, the worm wheel and the worm form a transmission pair and are arranged in the support box body, the motor is connected with the worm, the screw nut and the screw form another transmission pair, and the screw nut is installed in the support box body through the radial thrust ball bearing.
Preferably, the test bed base is provided with a movable guide rail, and the engine support is mounted on the movable guide rail to perform horizontal displacement motion in the left-right direction.
As a further preference, the upper surface of one end of the heat preservation box body is rotatably connected with a rotating shaft, the heat preservation box body is rotatably connected with the cover body through the rotating shaft, the outer surface of the cover body is fixedly connected with an elastic hook, the bottom of the elastic hook is arranged in an inclined plane structure, a clamping block is integrally formed on the outer surface of the heat preservation box body close to the elastic hook, and the elastic hook is movably connected with the clamping block.
Preferably, the thickness of the inner layer of each heat-insulating layer is (50 +/-2) mm, and the circumferential butt joint surfaces of the front end, the rear end and the two sides of each heat-insulating layer are inclined planes of 45 degrees.
As a further optimization, the heat preservation box further comprises a control panel and a temperature sensor, wherein the control panel is installed on the outer wall of the heat preservation box body, the temperature sensor is installed on one side of the outer wall surface of the engine, and the temperature sensor is in signal connection with the control panel; a controller and an integrated system are installed in the control panel;
the controller is used for receiving signals sent by the thrust sensor and simultaneously providing different engine control signals for the integrated system;
the integrated system is used for controlling the adjustment of the thrust bracket while controlling the operation of the engine under different working conditions according to different engine control signals;
the controller is used for transmitting a sensing signal.
Preferably, the heating and cooling system comprises a circulation pipeline, and a compressor, a four-way valve, a heat dissipation pipe, a first fan, a liquid storage tank and a liquid nitrogen tank which are sequentially arranged on the circulation pipeline, wherein a heating wire is arranged inside the liquid storage tank and used for exchanging heat with a circulation medium, and the heating wire is respectively and electrically connected with the control panel.
As a further preference, the heating and cooling system includes a throttle valve, one end of which is connected to the tank and the other end of which is connected to the first three-way valve.
A temperature control method for a solid rocket engine ground test rig, the method comprising:
step S1, the preset formula is: a ═ T (x) F, where a represents a temperature adjustment parameter, T represents a preset temperature of the engine (external surface), T represents an actual temperature of the engine (external surface), and F is an adjustment coefficient;
step S2, closing the door of the heat preservation cabin and checking the heat preservation cabin to ensure no leakage place;
step S3, acquiring the actual temperature t of the outer surface of the engine through a temperature sensor;
step S4, if the actual temperature T of the outer surface of the engine is lower than the preset temperature T of the outer surface of the engine, obtaining a result A through a formula, and heating the environment in the heat insulation box through a heating mode; if the heating power of the compressor is not enough, the heating wire is started to heat the circulating medium.
The actual temperature T of the outer surface of the engine is higher than the preset temperature T of the outer surface of the engine, the cooling mode is started to cool the interior of the heat insulation box through the result A of the formula, and if the cooling power is insufficient, the interior of the heat insulation box is cooled through the liquid nitrogen loop through the adjustment of the first three-way valve and the second three-way valve.
The technical scheme has the following advantages or beneficial effects:
(1) in the invention, the heat insulation box is of a detachable structure, when the engine needs heat insulation, the heat insulation box is closed, the heat dissipation and heat insulation coil is communicated with the outside, the interior of the heat insulation box is heated or cooled, and the heat insulation of the engine is carried out according to the test requirements. And opening the heat preservation box after heat preservation is finished, removing the heat preservation wall at the spray pipe, and performing an ignition test on the engine if other side walls are removed according to the condition.
(2) The heat preservation box is arranged, so that the problem that the engine does not work only in a normal-temperature environment, but usually works in a high-temperature or low-temperature environment and other external environments is solved.
(3) In the invention, the ground test bed of the solid rocket engine is integrated with the high-temperature box and the low-temperature box, so that the preparation processes of the engine after heat preservation and before test can be reduced, the test temperature of the engine is closer to the use temperature, and the transfer process of the engine is also reduced.
(4) In the invention, a test bed support is arranged: the main function supports the tested engine, and can be adjusted front and back, left and right to adapt to engines of different sizes.
(5) The invention is provided with a baffle plate which is mainly used for fixing the thrust sensor and giving a fixed counter force to prevent the engine from moving forwards and backwards during the engine test. The thrust sensor is movable on the baffle to accommodate alignment with the engine center.
(6) In the invention, the second fan ensures the temperature in the heat insulation box to be uniform.
(7) According to the invention, the control acquisition system of the thermal insulation cabin and the control acquisition system of the engine test bed can be integrated into one system, so that the cost is saved.
Drawings
FIG. 1 is a schematic structural view of a solid rocket engine ground test stand according to the present invention;
FIG. 2 is a cross-sectional view of a solid rocket engine ground test stand according to the present invention;
fig. 3 is a schematic view of the heating and refrigerating system of the present invention.
In the figure: 1. a test bed base; 2. an engine mount; 3. a thrust bracket; 4. a thrust sensor; 5. an engine; 6. a coil pipe; 7. a first three-way valve; 8. a second three-way valve; 9. a heat-insulating layer; 10. a heating and cooling system; 11. a compressor; 12. a four-way valve; 13. a radiating pipe; 14. a first fan; 15. a liquid storage tank; 16. heating wires; 17. a throttle valve; 18. a liquid nitrogen tank; 19. a second fan; 20. and controlling the acquisition system.
Detailed Description
In order to make the aforementioned objects, features and advantages of the present invention comprehensible, embodiments accompanied with figures are described in detail below.
In the description of the present invention, it is to be understood that the terms "upper", "lower", "front", "rear", and the like, which indicate orientations or positional relationships, are based on the orientations or positional relationships shown in the drawings, are only for convenience in describing the present invention and simplifying the description, and do not indicate or imply that the referred devices or elements must have a specific orientation, be constructed in a specific orientation, and be operated, and thus, should not be construed as limiting the present invention.
The terms "first", "second" and "first" are used for descriptive purposes only and are not to be construed as indicating or implying relative importance or to implicitly indicate the number of technical features indicated. Thus, a feature defined as "first" or "second" may explicitly or implicitly include at least one of the feature.
Referring to fig. 1-3, a ground test stand for a solid rocket engine comprises,
in the embodiment, a heating and refrigerating system 10 is arranged on the outer wall of one side of a heat preservation box body, a first three-way valve 7 is arranged at one end of the heating and refrigerating system 10, a second three-way valve 8 is arranged at the other end of the heating and refrigerating system 10, the first three-way valve 7 is connected with one end of a cooling pipe, the cooling pipe penetrates through one side of the heat preservation box body and is arranged in the inner wall of the heat preservation box body in a surrounding mode to form a coil pipe 6, and the other end of the cooling pipe is connected with the second three-way valve 8; a circulating medium is arranged in the cooling pipe in a flowing way,
one side of the heat preservation box body is movably connected with the cover body; the inner walls of the heat preservation box body and the cover body are both provided with a heat preservation layer 9;
a test frame; the test stand is arranged in the insulation can and comprises a test stand base 1, an engine support 2 and a thrust support 3, the engine support 2 and the thrust support 3 are both arranged on the test stand base 1, the output end of the thrust support 3 is connected with the engine support 2, a baffle is arranged on the thrust support, and a thrust sensor 4 is arranged on the baffle;
An engine; an engine is mounted on the engine mount 2.
Wherein, the insulation can is a detachable box body, and the insulation can is a polygonal box body formed by connecting a plurality of connecting blocks end to end.
Further, as a preferred embodiment, the heat preservation box body is divided into an outer layer, an interlayer and an inner layer from outside to inside, the inner layer is a heat preservation layer 9, the interlayer is composed of vacuum interlayers, and the outer layer is composed of heat preservation plates and encloses the box body to form an inner cavity capable of containing the engine 5.
Further, as a preferred implementation mode, the thrust support 3 includes a support box, a worm wheel, a worm, a motor, a lead screw nut, a radial thrust ball bearing and a lead screw, the support box is mounted on the test bed base 1, the worm wheel and the worm form a transmission pair and are arranged in the support box, the motor is connected with the worm, the lead screw nut and the lead screw form another transmission pair, and the lead screw nut is mounted in the support box through the radial thrust ball bearing.
Wherein, thrust bracket 3 is used for controlling engine support 2: the engine support 2 can be adjusted front, back, left and right according to the size change of the test engine so as to adapt to engines with different sizes
Further, as a preferred embodiment, a movable guide rail is arranged on the test bed base 1, and the engine support 2 is mounted on the movable guide rail to perform horizontal displacement motion in the left-right direction.
Further, as a preferred embodiment, the upper surface of one end of the heat preservation box body is rotatably connected with a rotating shaft, the heat preservation box body is rotatably connected with the cover body through the rotating shaft, the outer surface of the cover body is fixedly connected with an elastic clamping hook, the bottom of the elastic clamping hook is arranged in an inclined plane structure, a clamping block is integrally formed on the outer surface of the heat preservation box body close to the elastic clamping hook, and the elastic clamping hook is movably connected with the clamping block.
Further, as a preferred embodiment, the thickness of the inner layer of the insulating layer 9 is (50 ± 2) mm, and the circumferential abutting surfaces of the front end, the rear end and the two sides of each insulating layer 9 are inclined surfaces of 45 degrees.
Further, as a preferred embodiment, the engine further comprises a control panel and a temperature sensor, wherein the control panel is installed on the outer wall of the heat insulation box body, the temperature sensor is installed on the outer wall surface of the engine 5, and the temperature sensor is in signal connection with the control panel; a controller and an integrated system are arranged in the control panel;
the controller is used for receiving the signal sent by the thrust sensor 4 and simultaneously providing different engine 5 control signals for the integrated system;
the controller is used for receiving the signal sent by the thrust sensor 4 and simultaneously providing different engine 5 control signals for the integrated system;
the integrated system is used for controlling the adjustment of the thrust bracket 3 while controlling the operation of the engine 5 under different working conditions according to different control signals of the engine 5;
The controller is used for transmitting a sensing signal;
wherein, constitute a control collection system 20 by controller, integrated system jointly, control collection system 20 is integrated in control panel, and control collection system 20 carries out the collection of transmission signal through controller and integrated system.
Further, as a preferred embodiment, the heating and cooling system 10 includes a circulation line, and a compressor 11, a four-way valve 12, a heat dissipation pipe 13, a first fan 14, a liquid storage tank 15 and a liquid nitrogen tank 18 which are sequentially disposed on the circulation line, wherein a heating wire 16 is disposed inside the liquid storage tank 15, the heating wire 16 is used for performing heat exchange with a circulation medium, and the heating wires 16 are respectively electrically connected with a control panel.
Further, as a preferred embodiment, the heating and cooling system further includes a throttle valve 17, one end of the throttle valve 17 is connected to the reservoir 15, and the other end of the throttle valve 17 is connected to the first three-way valve 7.
The heating and refrigerating system 10 further comprises a second fan 19, the second fan 19 is installed in the heat insulation layer 9, and the second fan 19 is used for controlling air flow in the heat insulation layer 9; the mounting of the second fan 19 facilitates the uniformity of the temperature spread.
A temperature control method for a solid rocket engine ground test bench comprises the solid rocket engine ground test bench, and comprises the following steps:
Step S1, the preset formula is: a ═ T) xf, where a represents a temperature adjustment parameter, T represents a preset temperature of the engine (external surface), T represents an actual temperature of the engine (external surface), and F is an adjustment coefficient;
step S2, acquiring the actual temperature of the engine (external surface) through a temperature sensor;
step S3, if the actual temperature of the engine (outer surface) is lower than the preset temperature of the engine (outer surface), obtaining a result A through a formula, and heating the environment in the heat preservation box through a heating mode; if the heating power of the compressor is insufficient, the heating wire 16 is started to heat the circulating medium.
If the actual temperature of the engine (outer surface) is higher than the preset temperature of the engine (outer surface), the cooling mode is started to cool the interior of the heat insulation box through the result A of the formula, and if the cooling power is insufficient, the interior of the heat insulation box is cooled through the liquid nitrogen loop through the adjustment of the three-way valve 7 and the three-way valve 8.
Wherein, the circulating medium is glycol type cooling liquid or other cooling liquids.
In the first embodiment, when the engine 5 needs to be insulated, the insulation box is closed, the heat-dissipation and insulation coil 6 heats or cools the interior of the insulation box through a valve and a heating system, and the engine 5 is insulated according to the test requirements. And opening the heat preservation box after heat preservation is finished, removing the heat preservation wall at the spray pipe, and carrying out an ignition test on the engine 5 according to whether other side walls are removed or not.
Before the floor test of the engine 5, the engine 5 is kept warm. The engine mount 2 is adjusted to a proper position, and the test engine 5 is placed on the engine mount 2. A temperature sensor is attached to a position corresponding to the outer surface of the test engine 5, and the position of the thrust sensor 4 on the thrust support 3 is adjusted, so that the thrust sensor 4 and the test engine 5 are aligned, and the subsequent thrust measurement is convenient. And closing the incubator. When the required temperature is not very high, the working medium circulation path is as follows: a heat dissipation (cooling) coil 6, a first three-way valve 7, a heating and refrigerating system 10 and a second three-way valve 8 start a compressor 11 to carry out conventional refrigeration (heating); when the required temperature is higher, an electric heating wire 16 in the liquid storage tank is opened to electrically heat the circulating medium; when the required temperature is lower, the working medium circulation path is as follows: the heat dissipation (cooling) coil 6, the first three-way valve 7, the liquid nitrogen tank 18 and the second three-way valve 8 are refrigerated by liquid nitrogen. After the heat preservation is finished, the heat preservation box is opened, one fan of the heat preservation layer 9 close to the outlet of the engine 5 spray pipe is removed, and the side walls of other heat preservation layers 9 are removed according to the situation. The engine 5 can directly carry out ignition test because the sensors are connected before and the thrust sensor 4 is centered. The preparation time after the product is taken out of the cabin (the heat preservation cabin) is reduced.
In the second embodiment, the circulation is performed at a temperature close to normal temperature ranging from-20 ℃ to 30 ℃ and when the temperature is higher than 30 ℃, and the working medium circulation path of the electric heating wire can be started as follows: a heat dissipation (cooling) coil 6, a first three-way valve 7, a heating and refrigerating system 10 and a second three-way valve 8 start a compressor 11 to carry out conventional refrigeration (heating);
in the third embodiment, when the required temperature is lower than-20 ℃, the working medium circulation path is as follows: the heat dissipation (cooling) coil 6, the first three-way valve 7, the liquid nitrogen tank 18 and the second three-way valve 8 are refrigerated by liquid nitrogen. After the heat preservation is finished, the heat preservation box is opened, one fan of the heat preservation layer 9 close to the outlet of the engine 5 spray pipe is removed, and whether the side walls of other heat preservation layers 9 are removed depends on the situation.
While the invention has been described with reference to a preferred embodiment, it will be understood by those skilled in the art that various changes in form and detail may be made without departing from the spirit and scope of the invention.
Claims (10)
1. A solid rocket engine ground test bench is characterized by comprising:
the heating and refrigerating system (10) is arranged on the outer wall of one side of the heat preservation box body, a first three-way valve (7) is arranged at one end of the heating and refrigerating system (10), a second three-way valve (8) is arranged at the other end of the heating and refrigerating system (10), the first three-way valve (7) is connected with one end of a cooling pipe, the cooling pipe penetrates through one side of the heat preservation box body and is arranged in the inner wall of the heat preservation box body in a surrounding mode to form a coil pipe (6), and the other end of the cooling pipe is connected with the second three-way valve (8); a circulating medium flows in the cooling pipe,
The cover body, one side of the said insulated cabinet makes the removable connection with said cover body; the inner walls of the heat preservation box body and the cover body are both provided with a heat preservation layer (9);
a test stand; the test rack is installed in the heat-insulation box body and comprises a test bench base (1), an engine support (2) and a thrust support (3), the engine support (2) and the thrust support (3) are installed on the test bench base (1), the output end of the thrust support (3) is connected with the engine support (2), a baffle is arranged on the thrust support (3), and a thrust sensor (4) is arranged on the baffle;
an engine (5); the engine (5) is mounted on the engine support (2).
2. The solid rocket engine ground test bench of claim 1, wherein the insulation box body is divided into an outer layer, an interlayer and an inner layer from outside to inside, the inner layer is an insulation layer (9), the interlayer is composed of vacuum interlayers, the outer layer is composed of insulation boards, and the box body is enclosed to form an inner cavity capable of containing the engine.
3. The solid rocket engine ground test bench of claim 1, wherein the thrust support (3) comprises a support box, a worm gear, a worm, a motor, a lead screw nut, a radial thrust ball bearing and a lead screw, the support box is mounted on the test bench base (1), the worm gear and the worm form a transmission pair and are arranged in the support box, the motor is connected with the worm, the lead screw nut and the lead screw form another transmission pair, and the lead screw nut is mounted in the support box through the radial thrust ball bearing.
4. The ground test bench for solid rocket engines according to claim 1, wherein a moving guide rail is provided on the base (1) of the test bench, and the engine mount (2) is mounted on the moving guide rail for horizontal displacement motion in the left-right direction.
5. The ground test bench for solid rocket engines as claimed in claim 1, wherein a rotating shaft is rotatably connected to the upper surface of one end of the thermal insulation box body, the thermal insulation box body is rotatably connected to the cover body through the rotating shaft, an elastic hook is fixedly connected to the outer surface of the cover body, the bottom of the elastic hook is arranged in an inclined plane structure, a clamping block is integrally formed on the outer surface of the thermal insulation box body close to the elastic hook, and the elastic hook is movably connected to the clamping block.
6. The ground test bench for solid rocket engines according to claim 2, wherein the thickness of the inner layer of the insulating layer (9) is (50 ± 2) mm, and the circumferential butt-joint surfaces of the front end, the rear end and the two sides of each insulating layer (9) are both 45 ° inclined surfaces.
7. The solid-rocket engine ground test stand of claim 1, further comprising a control panel and a temperature sensor, wherein the control panel is installed on the outer wall of the heat-insulating box body, the temperature sensor is installed on one side of the outer wall surface of the engine, and the temperature sensor is in signal connection with the control panel; a controller and an integrated system are installed in the control panel;
The controller is used for receiving a signal sent by a thrust sensor (4) and simultaneously providing different engine control signals for the integrated system;
the integrated system is used for controlling the operation of the engine under different working conditions and controlling the adjustment of the thrust bracket (3) according to different engine control signals;
the controller is used for transmitting a sensing signal.
8. The ground test bench for solid rocket engines according to claim 7, wherein the heating and cooling system (10) comprises a circulation pipeline, and a compressor (11), a four-way valve (12), a heat dissipation pipe (13), a first fan (14), a liquid storage tank (15) and a liquid nitrogen tank (18) which are sequentially arranged on the circulation pipeline, wherein a heating wire (16) is arranged inside the liquid storage tank (15), the heating wire (16) is used for exchanging heat with a circulation medium, and the heating wire (16) is respectively and electrically connected with the control panel.
9. The solid-rocket engine ground test stand of claim 8, wherein said heating and cooling system (10) comprises a throttle valve (17), one end of said throttle valve (17) is connected to said liquid storage tank (15), and the other end of said throttle valve (17) is connected to said first three-way valve (7).
10. A method of temperature control for a solid rocket engine ground test rig of claim 1, the method comprising:
step S1, the preset formula is: a ═ T) xf, where a represents a temperature adjustment parameter, T represents a preset temperature of the engine (external surface), T represents an actual temperature of the engine (external surface), and F is an adjustment coefficient;
step S2, closing the door of the heat preservation cabin and checking the heat preservation cabin to ensure no leakage place;
step S3, acquiring the actual temperature t of the outer surface of the engine through a temperature sensor;
step S4, if the actual temperature T of the outer surface of the engine (5) is lower than the preset temperature T of the outer surface of the engine (5), obtaining a result A through a formula, and heating the environment in the heat insulation box through a heating mode; if the heating power of the compressor is insufficient, starting a heating wire (16) to heat the circulating medium;
the actual temperature T of the outer surface of the engine (5) is higher than the preset temperature T of the outer surface of the engine (5), the cooling mode is started to cool the interior of the heat preservation box through the result A of the formula, and if the cooling power is insufficient, the interior of the heat preservation box is cooled through the liquid nitrogen loop through the adjustment of the first three-way valve (7) and the second three-way valve (8).
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
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