Rocket engine simulation test device and method
The rocket engine simulation test device, which combines a simulated cabin shell with volumetric blocks, solves the problem of the lack of versatility of traditional devices and realizes the wide applicability and cost-effectiveness of simulation test devices for different rocket engines.
Patent Information
- Authority / Receiving Office
- CN · China
- Patent Type
- Patents(China)
- Current Assignee / Owner
- WUHAN GUIDE INFRARED CO LTD
- Filing Date
- 2023-04-07
- Publication Date
- 2026-06-12
AI Technical Summary
Traditional rocket engine simulation test equipment lacks versatility, requiring the design of a separate simulator for each type of engine, resulting in equipment waste and increased development costs.
The device combines a simulated chamber shell with various volume blocks of different sizes. By changing the volume blocks, different initial cavity volumes can be simulated. Combined with pressure measuring end cap assembly, sealing end cap, interstage isolator and simulated nozzle, a variety of simulation test devices are formed.
It has achieved wide applicability of simulation test devices for different rocket engines, reduced the number of devices, and lowered development costs.
Smart Images
Figure CN116378857B_ABST
Abstract
Description
Technical Field
[0001] This invention belongs to the field of rocket engine technology, specifically relating to a rocket engine simulation test device and method. Background Technology
[0002] Solid rocket motors are widely used as power units in various missile weapon systems, such as Figure 1 This is a dual-pulse type solid rocket motor, which mainly includes an ignition device 100, an interstage isolation mechanism 200, a combustion chamber 300, a propellant charge 400, a plug 500, and a nozzle 600. Among them, the interstage isolation mechanism 200, the ignition device 100, and the plug 500 need to undergo simulation tests after the design is completed to verify whether the design meets the usage requirements. At the same time, after production, they also need to undergo simulation tests for acceptance.
[0003] Generally, the simulation test equipment used in simulation tests must ensure that its cavity volume is the same as that of the actual engine. Therefore, different solid rocket engine schemes require different simulation test equipment. At the same time, different types of simulation test equipment also need to be designed when conducting preliminary investigations or acceptance tests on solid rocket engine components such as ignition device 100, interstage isolation mechanism 200, and plug 500.
[0004] It is evident that traditional simulation test devices lack versatility, requiring the design and fabrication of a separate simulation tester for each test or each engine. This results in significant equipment waste and increases engine development costs. Summary of the Invention
[0005] This invention relates to a rocket engine simulation test apparatus and method, which can at least solve some of the defects of the prior art.
[0006] This invention relates to a rocket engine simulation test apparatus, comprising:
[0007] Simulated cabin hull;
[0008] Multiple volume blocks, each having a hollow channel for simulating a rocket engine cavity, and each volume block having a different hollow channel specification; each volume block can be selectively and detachably installed inside the simulation cabin shell.
[0009] As one embodiment, the simulation cabin shell includes a first compartment and a second compartment suitable for coaxial detachable connection; each volume block includes a variety of first volume blocks adapted to the first compartment and a variety of second volume blocks adapted to the second compartment, wherein each first volume block is detachably installed in the first compartment and each second volume block is detachably installed in the second compartment.
[0010] As one embodiment, the rocket engine simulation test device also includes a pressure measuring end cap assembly, which includes a pressure measuring end cap adapted to be connected to the end of the simulation cabin shell, a pressure measuring unit disposed on the pressure measuring end cap, and an ignition charge disposed inside the pressure measuring end cap.
[0011] As one embodiment, the rocket engine simulation test device also includes a sealed end cap and a simulated nozzle for simulating a rocket engine nozzle, wherein the sealed end cap and the simulated nozzle are optionally installed at the other end of the simulation chamber shell.
[0012] As one implementation method, the rocket engine simulation test device also includes an interstage isolator; the simulation cabin shell includes a first section and a second section that are coaxially and detachably connected in series, and the interstage isolator is configured to be sandwiched between the first section and the second section.
[0013] As one implementation method, the pressure measuring end cap assemblies are installed at both ends of the simulation chamber shell.
[0014] The present invention also relates to a rocket engine simulation test method, which is implemented based on the above-mentioned rocket engine simulation test device. By replacing the volume blocks of different specifications, the ignition closed burst test of rocket engines with different initial cavity volumes can be carried out.
[0015] As one implementation method, the end cap of the simulated chamber shell, which is far from the ignition end, is replaced with a simulated nozzle to conduct a plugging test and acceptance test.
[0016] As one embodiment, the rocket engine simulation test device further includes an interstage isolator; the simulation cabin shell includes a first section and a second section that are coaxially and detachably connected in series, and the interstage isolator is configured to be sandwiched between the first section and the second section.
[0017] As one implementation method, pressure measuring end cap assemblies are installed at both ends of the simulation chamber shell to conduct interstage isolator preliminary and acceptance tests; wherein, the pressure measuring end cap assembly includes a pressure measuring end cap suitable for connection to the end of the simulation chamber shell, a pressure measuring unit disposed on the pressure measuring end cap, and an ignition charge disposed inside the pressure measuring end cap.
[0018] The present invention has at least the following beneficial effects:
[0019] This invention uses a combination of a simulated cabin shell and volume blocks to form a simulated cabin. By replacing volume blocks of different specifications, it is possible to conduct sealed explosion tests of rocket engines with different initial cavity volumes. It has a very wide range of applications, requires fewer pieces of equipment, and is inexpensive, resulting in a high cost-effectiveness ratio.
[0020] In this invention, when the rocket engine simulation test device is equipped with a simulation cabin, pressure measuring end cover assembly, sealing end cover, interstage isolator and simulation nozzle, it can be assembled into simulation test devices with different structures according to the combination of simulation cabin shell and different components, thereby meeting the requirements of various simulation tests of rocket engines, greatly reducing equipment waste and lowering the development cost of rocket engines. Attached Figure Description
[0021] To more clearly illustrate the technical solutions in the embodiments of the present invention or the prior art, the drawings used in the description of the embodiments or the prior art will be briefly introduced below. Obviously, the drawings described below are only some embodiments of the present invention. For those skilled in the art, other drawings can be obtained based on these drawings without creative effort.
[0022] Figure 1 A structural schematic diagram of a solid rocket motor provided for the background art;
[0023] Figure 2 This is a schematic diagram of the structure of the simulation cabin provided in an embodiment of the present invention;
[0024] Figure 3 This is a schematic diagram of the structure of the pressure measuring end cap assembly provided in an embodiment of the present invention;
[0025] Figure 4 This is a schematic diagram of the structure of the sealing end cap provided in an embodiment of the present invention;
[0026] Figure 5 This is a schematic diagram of the structure of a simulated nozzle provided in an embodiment of the present invention;
[0027] Figure 6 This is a schematic diagram of the structure of an interstage isolator provided in an embodiment of the present invention;
[0028] Figure 7 and Figure 8 A schematic diagram of the structure of a rocket engine simulation test device for conducting a closed-circuit ignition test.
[0029] Figure 9 A schematic diagram of the rocket engine simulation test device used for preliminary sealing and acceptance tests;
[0030] Figure 10 A schematic diagram of the rocket engine simulation test device used for preliminary and acceptance tests of the interstage isolator. Detailed Implementation
[0031] The technical solutions in the embodiments of the present invention will be clearly and completely described below. Obviously, the described embodiments are only some embodiments of the present invention, and not all embodiments. Based on the embodiments of the present invention, all other embodiments obtained by those skilled in the art without creative effort are within the scope of protection of the present invention.
[0032] Example 1
[0033] like Figure 2 , Figures 7-10 This invention provides a rocket engine simulation test apparatus, comprising:
[0034] Simulated cabin hull;
[0035] Multiple volume blocks, each having a hollow channel for simulating a rocket engine cavity, and each volume block having a different hollow channel specification; each volume block can be selectively and detachably installed inside the simulation cabin shell.
[0036] The aforementioned volume blocks include, but are not limited to, those made of ABS (Acrylonitrile Butadiene Styrene) or nylon, which, while meeting the requirements of simulation tests, have the advantages of low cost.
[0037] The aforementioned volumetric block is preferably tightly fitted within the simulation chamber shell to ensure its positional stability during the simulation test, thereby guaranteeing the accuracy and reliability of the test results. Preferably, limiting rings are provided at both ends of the simulation chamber shell to restrict the axial movement of the volumetric block.
[0038] The aforementioned simulation cabin shell plus volume blocks constitute a simulation cabin 1.
[0039] In one embodiment, such as Figure 2 Near the ignition end of the simulation chamber shell, the hollow channel adopts a tapering cavity section, with the tapering direction from the outside to the inside. The ignition charge 22 at the ignition end of the simulation chamber shell is preferably located within this tapering cavity section. Furthermore, the tail end of this tapering cavity section is sequentially connected to a constant cross-section cavity section and a gradually expanding cavity section. This method can better simulate the sealed explosion test of the igniter.
[0040] In one embodiment, such as Figure 2The simulated cabin shell includes a first section 11 and a second section 13 that are coaxially and detachably connected in series; each volume block includes a variety of first volume blocks 12 adapted to the first section 11 and a variety of second volume blocks 14 adapted to the second section 13, wherein each first volume block 12 is selectively and detachably installed in the first section 11, and each second volume block 14 is selectively and detachably installed in the second section 13.
[0041] The first compartment 11 and the second compartment 13 may have the same or different lengths, and their cross-sectional shapes and dimensions are preferably the same. The first compartment 11 and the second compartment 13 are preferably connected by a flange, and the two can be sealed by means of clamping a sealing ring or other methods.
[0042] Preferably, both the first section 11 and the second section 13 can be used individually for the sealed ignition test of the rocket engine, or they can be used together for the sealed ignition test of the rocket engine. In one embodiment, the first section 11 can be used with an initial cavity volume of 100 cm³. 3 ~1000cm 3 The rocket engine ignition seal burst test; the second section 13 can be used for an initial cavity volume of 900 cm³. 3 ~2000cm 3 The closed-loop explosion test of the rocket engine igniter; when the first section 11 and the second section 13 are combined, it can be used for an initial cavity volume of 1000 cm³. 3 ~3000cm 3 The sealed ignition test of the rocket engine's ignition device was conducted. It is evident that, based on the above scheme, an initial cavity volume of 100 cm³ can be achieved. 3 ~3000cm 3 The closed-loop explosion test of the rocket engine igniter has a very wide range of applications.
[0043] During simulation tests, both ends of the simulation chamber shell generally need to be sealed. One end of the simulation chamber shell is defined as the ignition end, and the other end as the sealed end. The ignition end needs to be equipped with an ignition charge 22.
[0044] Among them, such as Figure 4 The aforementioned rocket engine simulation test device also includes a sealing end cap 3, which mainly serves to seal the end of the simulation cabin shell. It is suitable for detachable connection with the simulation cabin shell, including but not limited to flange connection.
[0045] In one embodiment, such as Figure 3The rocket engine simulation test device also includes a pressure measuring end cover assembly 2, which includes a pressure measuring end cover 21 adapted to be connected to the end of the simulation cabin shell, a pressure measuring unit disposed on the pressure measuring end cover 21, and an ignition charge 22 disposed inside the pressure measuring end cover 21.
[0046] The pressure measuring end cap 21 is preferably detachably connected to the shell of the simulation chamber, including but not limited to using flange connection.
[0047] Preferably, such as Figure 3 The pressure measuring unit includes a pressure sensor 23 and a pressure measuring adapter 24. The pressure measuring adapter 24 is connected to the pressure measuring end cap 21, including but not limited to connection methods such as threaded fixing. The pressure sensor 23 is installed on the pressure measuring adapter 24.
[0048] Preferably, such as Figure 3 A wire passage hole is provided on the pressure measuring end cap 21. The wire passage hole is preferably a stepped hole. A sealing plug 25 is filled in the outer large hole, and a clamping bolt 26 is screwed on the outer opening of the wire passage hole to fully clamp the sealing plug 25. Both the sealing plug 25 and the clamping bolt 26 are provided with wire routing holes. The wires on the ignition charge 22 pass through the wire routing holes on the sealing plug 25 and the clamping bolt 26 in sequence.
[0049] In one embodiment, such as Figure 5 The aforementioned rocket engine simulation test device also includes a simulated nozzle 4, used to simulate the nozzle of a rocket engine. Preferably, as shown... Figure 5 The simulated nozzle 4 includes a base cover 41, a nozzle body 42 formed on the base cover 41, and a plug 43 disposed in the nozzle body 42. Preferably, the nozzle body 42 is integrally formed with the base cover 41. The nozzle body 42 has a converging section and an expanding section. The plug 43 is fixed on the converging section (including but not limited to fixing by means of adhesive bonding). An anti-cone ring 44 (including but not limited to fixing by means of adhesive bonding) is also fixed in the expanding section. The anti-cone ring 44 abuts against the outer shoulder of the plug 43.
[0050] Preferably, the aforementioned rocket engine simulation test device is equipped with both the sealing end cap 3 and the simulated nozzle 4, with one of them selectively installed at the other end (i.e., the closed end) of the simulation chamber shell. When the sealing end cap 3 is installed at the closed end of the simulation chamber shell, a sealed explosion test of the rocket engine igniter can be conducted; when the simulated nozzle 4 is installed at the closed end of the simulation chamber shell, a plugging test and acceptance test can be conducted. It is evident that different simulation tests of the rocket engine can be performed simply by replacing different end caps at the closed end, demonstrating high versatility and flexibility.
[0051] In one embodiment, such as Figure 6The rocket engine simulation test device also includes an interstage isolator 5; the simulation chamber shell includes a first section 11 and a second section 13 that are coaxially and detachably connected in series, and the interstage isolator 5 is configured to be sandwiched between the first section 11 and the second section 13.
[0052] Preferably, the interstage isolator 5 includes a connecting ring 51 and an isolation mechanism 52. The isolation mechanism 52 is installed on the connecting ring 51 and closes the inner ring of the connecting ring 51. The installation method includes, but is not limited to, screw / bolt fixing. For example, threaded holes are provided around the inner ring of the connecting ring 51 and threaded holes are provided around the edge of the isolation mechanism 52. The number of threaded holes on the connecting ring 51 and the isolation mechanism 52 are the same and distributed one-to-one. The isolation mechanism 52 can be fixed to the connecting ring 51 by multiple screws. The outer ring of the connecting ring 51 is provided with a connecting structure for connecting with the first compartment 11 and the second compartment 13. For example, the outer ring of the connecting ring 51 adopts a flange ring structure, and the first compartment 11, the connecting ring 51 and the second compartment 13 are assembled by flanges.
[0053] By configuring the interstage isolator 5, the isolation mechanism 52 of the rocket engine can be tested and accepted. Preferably, the end cap at the closed end of the simulated cabin shell has a pressure detection function, for example, by installing a pressure measuring unit on this end cap; as a preferred embodiment, such as... Figure 10 The pressure measuring end cap assembly 2 is installed at both ends of the simulation chamber shell, so that there is no need to configure another end cap, which can reduce the number of required equipment. Moreover, the pressure measuring end cap assembly 2 at the closed end can be reused. For example, after the preliminary and acceptance test of the isolation mechanism 52, the pressure measuring end cap assembly 2 can be installed at the ignition end of the simulation chamber shell for use.
[0054] In this embodiment, preferably, the above-mentioned rocket engine simulation test device is equipped with a pressure measuring end cap assembly 2, a sealing end cap 3, an interstage isolator 5, and a simulated nozzle 4. Depending on the combination of the simulation cabin shell and different components, simulation test devices with different structures can be assembled, thereby meeting the requirements of various simulation tests of rocket engines, greatly reducing equipment waste, and lowering the development cost of rocket engines.
[0055] Example 2
[0056] This invention provides a rocket engine simulation test method, which is implemented based on the rocket engine simulation test device described above.
[0057] Among them, by replacing the volume blocks of different specifications, closed-circuit ignition tests of rocket engines with different initial cavity volumes were conducted.
[0058] like Figure 7 and Figure 8Preferably, when conducting the igniter sealed explosion test, a combination structure of pressure measuring end cap assembly 2 + simulation chamber 1 + sealing end cap 3 is adopted.
[0059] In one embodiment, the end cap of the simulated chamber shell furthest from the ignition end is replaced with a simulated nozzle 4 to conduct plugging and acceptance testing. In this scheme, as... Figure 9 It adopts a combined structure of pressure measuring end cap assembly 2 + simulation chamber 1 + simulation nozzle 4.
[0060] Furthermore, such as Figure 10 For cases where an interstage isolator 5 is configured, pressure measuring end cap assemblies 2 are installed at both ends of the simulation chamber shell to conduct preliminary and acceptance tests on the interstage isolator 5, i.e., a combined structure of pressure measuring end cap assembly 2 + simulation chamber 1 + pressure measuring end cap assembly 2 is adopted.
[0061] The above description is only a preferred embodiment of the present invention and is not intended to limit the present invention. Any modifications, equivalent substitutions, improvements, etc., made within the spirit and principles of the present invention should be included within the protection scope of the present invention.
Claims
1. A rocket engine simulation test device, characterized in that, include: Simulated cabin hull; The simulated cabin shell includes a first and a second section that are coaxially and detachably connected in series. The system comprises multiple volume blocks, each having a hollow channel for simulating a rocket engine cavity, and each volume block having a different hollow channel specification. Each volume block includes multiple first volume blocks adapted to the first segment and multiple second volume blocks adapted to the second segment. A first volume block is detachably installed within the first segment, and this first volume block is any one of multiple first volume blocks of different specifications. A second volume block is detachably installed within the second segment, and this second volume block is any one of multiple second volume blocks of different specifications. The first segment and the first volume blocks installed within it, together with the second segment and the second volume blocks installed within it, constitute a simulation module. A pressure measuring end cap assembly, comprising a pressure measuring end cap adapted to be connected to the end of the simulation chamber shell, a pressure measuring unit disposed on the pressure measuring end cap, and an ignition charge disposed inside the pressure measuring end cap; When the simulation test device is used to conduct ignition closed burst tests, the simulation test device also includes a sealing end cover. The pressure measuring end cover and the sealing end cover are respectively detachably installed at both ends of the simulation chamber shell. By replacing volume blocks of different specifications, ignition closed burst tests of rocket engines with different initial cavity volumes can be conducted. When the simulation test device is used to conduct preliminary and acceptance tests on the inter-stage isolator, the simulation test device also includes the inter-stage isolator, which is sandwiched between the first compartment and the second compartment, and the pressure measuring end cap assembly is installed at both ends of the simulation compartment shell.
2. The rocket engine simulation test apparatus as described in claim 1, characterized in that, When the simulation test device is used for plugging and acceptance tests, the simulation test device also includes a simulated nozzle for simulating the nozzle of a rocket engine, and the pressure measuring end cap and the simulated nozzle are respectively installed at both ends of the simulation cabin shell.
3. A method for simulating rocket engine testing, characterized in that, It is implemented based on the rocket engine simulation test device described in claim 1. When the simulation test device adopts a combined structure including a simulation chamber, a pressure measuring end cap assembly and a sealing end cap, the ignition sealed explosion test of rocket engines with different initial cavity volumes can be carried out by replacing volume blocks of different specifications. When the simulation test device adopts a combined structure including a simulation chamber, an interstage isolator, and two sets of pressure measuring end cap assemblies, the preliminary and acceptance tests of the interstage isolator are carried out based on the simulation test device.
4. A method for simulating rocket engine testing, characterized in that, It is implemented based on the rocket engine simulation test device described in claim 2. When the simulation test device adopts a combined structure including a simulation chamber, a pressure measuring end cap assembly, and a simulation nozzle, a plugging and acceptance test is conducted based on the simulation test device.