阅读说明：本技术 一种固体火箭发动机燃烧的试验设备 (Test equipment for solid rocket engine combustion ) 是由 刘涛 陶玉惠 王成 胡红梅 于 2021-09-24 设计创作，主要内容包括：本发明公开了一种固体火箭发动机燃烧的试验设备,包括燃烧箱,所述燃烧箱的左侧固定连接有进料斗,所述进料斗的底部连通有弯管,所述弯管的右端贯穿燃烧箱并延伸至燃烧箱的内部,所述弯管的内部设置有阀门,所述燃烧箱的前侧设置有点火装置,所述燃烧箱内壁底部的前后左右侧均滑动连接有四个缓冲板,四个所述缓冲板相远离的一侧与燃烧箱的内壁之间均固定连接有第一弹簧,所述弯管的右端贯穿左侧缓冲板并延伸至缓冲板的右侧,本发明涉及火箭发动机技术领域。该固体火箭发动机燃烧的试验设备,通过置换机构的设置,实现了对喷射嘴的快速拆装,提升了工作效率,而且操作简单方便,实用性很强。(The invention discloses test equipment for combustion of a solid rocket engine, which comprises a combustion box, wherein the left side of the combustion box is fixedly connected with a feed hopper, the bottom of the feed hopper is communicated with a bent pipe, the right end of the bent pipe penetrates through the combustion box and extends to the inside of the combustion box, a valve is arranged inside the bent pipe, an ignition device is arranged on the front side of the combustion box, four buffer plates are slidably connected to the front side, the rear side, the left side and the right side of the bottom of the inner wall of the combustion box, a first spring is fixedly connected between the far side of each buffer plate and the inner wall of the combustion box, and the right end of the bent pipe penetrates through the left buffer plate and extends to the right side of the buffer plate. This test equipment of solid rocket engine burning through the setting of replacing the mechanism, has realized the quick assembly disassembly to the injection nozzle, has promoted work efficiency, and easy operation is convenient moreover, and the practicality is very strong.)

1. The utility model provides a test equipment of solid rocket engine burning, includes combustion box (1), left side fixedly connected with feeder hopper (2) of combustion box (1), the bottom intercommunication of feeder hopper (2) has return bend (3), the right-hand member of return bend (3) runs through combustion box (1) and extends to the inside of combustion box (1), the inside of return bend (3) is provided with valve (4), the front side of combustion box (1) is provided with ignition (5), its characterized in that: the combustion box comprises a combustion box (1), four buffer plates (6) are connected to the front, the rear, the left side and the right side of the bottom of the inner wall of the combustion box (1) in a sliding mode, first springs (7) are fixedly connected between the far sides of the four buffer plates (6) and the inner wall of the combustion box (1), the right end of an elbow (3) penetrates through the left buffer plate (6) and extends to the right side of the buffer plates (6), the outer surface of the elbow (3) is connected with the inner surface of the buffer plates (6) in a sliding mode, and a replacement mechanism (8) is arranged at the top of the combustion box (1);

including offering out flame mouth (81) at combustion box (1) top in replacement mechanism (8), annular (82) have been seted up at the top of combustion box (1) and the periphery that is located out flame mouth (81), the top swing joint of combustion box (1) has jet nozzle (83), the inside that annular (82) and extension to annular (82) are run through to the bottom of jet nozzle (83), square groove (84) have all been seted up to the top of combustion box (1) and the front and back side that is located annular (82), two the equal sliding connection in internal surface of square groove (84) has slider (85), two equal fixedly connected with gag lever post (86) of opposite side of slider (85), draw-in groove (87) have all been seted up to the front and back side of jet nozzle (83), two the looks remote site of gag lever post (86) all runs through annular (82) and extends to the inside of draw-in groove (87), the outer surfaces of the two limiting rods (86) are clamped with the inner surface of the clamping groove (87), and the outer surfaces of the two limiting rods (86) are connected with the inner surface of the combustion box (1) in a sliding mode.

2. A solid-rocket engine combustion test rig as recited in claim 1, wherein: the bottom of burning box (1) is provided with buffering supporting mechanism (9), including setting up bottom plate (91) in burning box (1) bottom in buffering supporting mechanism (9).

3. A solid-rocket engine combustion test rig as recited in claim 2, wherein: the top of the bottom plate (91) is provided with a groove (92), and a sliding plate (93) is connected between the inner walls of the groove (92) in a sliding manner.

4. A solid-rocket engine combustion test rig as recited in claim 1, wherein: the bottom of the combustion box (1) penetrates through the groove (92) and extends to the inside of the groove (92), and the bottom of the combustion box (1) is in contact with the top of the sliding plate (93).

5. A solid rocket engine combustion test rig according to claim 3, wherein: the left side and the right side of the bottom of the inner wall of the groove (92) are rotatably connected with rotating rods (94), and the bottom of the sliding plate (93) is provided with a sliding groove (95).

6. A solid-rocket engine combustion test rig as recited in claim 5, wherein: the left side and the right side of the inner surface of the sliding groove (95) are both connected with moving blocks (96) in a sliding mode, and the bottoms of the two moving blocks (96) are both connected with the top end of the rotating rod (94) in a rotating mode.

7. A solid-rocket engine combustion test rig as recited in claim 5, wherein: two fixedly connected with second spring (97) between one side of keeping away from mutually of bull stick (94) and the bottom of recess (92) inner wall, the left and right sides at bottom plate (91) top all rotates through pivot (98) and is connected with bracing piece (99).

8. A solid-rocket engine combustion test rig as recited in claim 7, wherein: chute (910) have all been seted up to the left and right sides of burning case (1), two the top of bracing piece (99) all runs through chute (910) and extends to the inside of chute (910), two the size of chute (910) slightly is greater than the size of bracing piece (99).

Technical Field

The invention relates to the technical field of rocket engines, in particular to a test device for combustion of a solid rocket engine.

Background

Solid rocket engines are chemical rocket engines that use solid propellants. Also known as solid propellant rocket engines. The solid propellant is ignited and then burnt in the combustion chamber, and chemical energy is converted into heat energy to produce high-temperature and high-pressure combustion products. The combustion products flow through the nozzle where they expand and accelerate, and the thermal energy is converted to kinetic energy and expelled from the nozzle at high velocity to produce thrust.

The rocket propellant needs to be tested in a large number of tests before application, the propellant combustion test is generally carried out in a combustion box, during the combustion process of the propellant, the propellant burns to generate a large amount of high-temperature high-pressure gas and is sprayed outwards at high speed, at the moment, huge pressure is generated in the combustion box instantly, the long-term test is easy to cause extrusion damage to the inner wall of the combustion box, in addition, the existing spray nozzle can intensively spray heat energy airflow, so that the spray efficiency is higher, although the spray nozzle adopts high-temperature resistant alloy materials, but the test time is long, or a new spray nozzle needs to be replaced to achieve a better spray effect, the existing spray nozzle is troublesome to disassemble and assemble, the working efficiency is reduced, in addition, the combustion box can sway left and right during spraying, the safety is not enough, but also has larger reaction force, can generate great pressure on the bottom plate, influences the service life of the bottom plate, to this end we propose a test apparatus for solid rocket engine combustion to solve the above problems.

Disclosure of Invention

Aiming at the defects of the prior art, the invention provides a test device for combustion of a solid rocket engine, which solves the problems that the inner wall of a combustion box is extruded and damaged, the existing injection nozzle is troublesome to disassemble and assemble, the combustion box can sway left and right during injection, the safety is not high, and the service life of a bottom plate is influenced.

In order to achieve the purpose, the invention is realized by the following technical scheme: a test device for combustion of a solid rocket engine comprises a combustion box, wherein a feed hopper is fixedly connected to the left side of the combustion box, the bottom of the feed hopper is communicated with a bent pipe, the right end of the bent pipe penetrates through the combustion box and extends to the inside of the combustion box, a valve is arranged inside the bent pipe, an ignition device is arranged on the front side of the combustion box, four buffer plates are slidably connected to the front, back, left and right sides of the bottom of the inner wall of the combustion box, a first spring is fixedly connected between one far side of each buffer plate and the inner wall of the combustion box, the right end of the bent pipe penetrates through the left buffer plate and extends to the right side of the buffer plate, the outer surface of the bent pipe is slidably connected with the inner surface of the buffer plate, and a replacement mechanism is arranged at the top of the combustion box; including seting up the play flame mouth at burning box top in the replacement mechanism, the annular has been seted up at the top of burning box and the periphery that is located a flame mouth, the top swing joint of burning box has jet nozzle, jet nozzle's bottom runs through the annular and extends to the inside of annular, square groove has all been seted up to the top of burning box and the side around being located the annular, two the equal sliding connection of internal surface of square groove has the slider, two the equal fixedly connected with gag lever post in opposite side of slider, the draw-in groove has all been seted up to the side around jet nozzle, two the inside that the annular extended to the draw-in groove is all run through to the looks remote site of gag lever post, two the surface of gag lever post all with the internal surface joint of draw-in groove, two the surface of gag lever post all with the internal surface sliding connection of burning box.

Preferably, the bottom of the combustion box is provided with a buffering support mechanism, and the buffering support mechanism comprises a bottom plate arranged at the bottom of the combustion box.

Preferably, the top of the bottom plate is provided with a groove, and a sliding plate is connected between the inner walls of the grooves in a sliding manner.

Preferably, the bottom of the combustion box penetrates through the groove and extends to the inside of the groove, and the bottom of the combustion box is in contact with the top of the sliding plate.

Preferably, the left side and the right side of the bottom of the inner wall of the groove are both rotatably connected with rotating rods, and the bottom of the sliding plate is provided with a sliding groove.

Preferably, the left side and the right side of the inner surface of the sliding groove are both connected with moving blocks in a sliding mode, and the bottoms of the two moving blocks are both rotatably connected with the top end of the rotating rod.

Preferably, two fixedly connected with second spring between the one side of keeping away from mutually of bull stick and the bottom of recess inner wall, the left and right sides at bottom plate top all is connected with the bracing piece through the pivot rotation.

Preferably, the chute has all been seted up to the left and right sides of combustion box, two the top of bracing piece all runs through the chute and extends to the inside of chute, two the size of chute slightly is greater than the size of bracing piece.

Advantageous effects

The invention provides a test device for combustion of a solid rocket engine. Compared with the prior art, the method has the following beneficial effects:

(1) this test equipment of solid rocket engine burning, through two sliders of dorsad slip, make two sliders drive the gag lever post and slide dorsad, finally make two gag lever posts slip from the draw-in groove, further upwards mention the jet nozzle, accomplish the dismantlement to the jet nozzle, during the installation, inject the jet nozzle inside the annular, further promote two sliders, make the slider drive two gag lever posts and slide into the draw-in groove and realized fixed the installation to the jet nozzle, setting through the replacement mechanism, realized the quick assembly disassembly to the jet nozzle, and the work efficiency is promoted, and easy operation is convenient, and the practicality is very strong.

(2) This test equipment of solid rocket engine burning, when the burning of burning box inside burning, burning box inside produces huge pressure gas in the twinkling of an eye, and four buffer boards of gaseous extrusion, four buffer boards begin to extrude the first spring of compression, through the setting of buffer board and first spring, have avoided damaging the burning box inner wall because of the huge pressure extrusion of the production in the twinkling of an eye of burning to the life of burning box has been improved.

(3) This test equipment of solid rocket engine burning, through rotating the bracing piece to the inside of chute, when the combustion box is inside to burn, the slide can be extruded to the anti-power of controlling of production, the slide begins to extrude movable block and bull stick downwards simultaneously, the bull stick begins to compress the second spring simultaneously, setting through buffering supporting mechanism, the extrusion force to the bottom plate in the twinkling of an eye of the combustion box has been reduced, the life of bottom plate has been prolonged, when the combustion box produces and rocks left and right rocking, the bracing piece reciprocates at the inside miniascape of chute, the bracing piece can support the protection to the combustion box simultaneously, the security has been strengthened.

Drawings

FIG. 1 is a perspective view of the external structure of the present invention;

FIG. 2 is an exploded view of the displacement mechanism of the present invention;

FIG. 3 is a perspective view of a baffle of the present invention;

FIG. 4 is a cross-sectional view of the base plate of the present invention;

fig. 5 is a partial enlarged view of the invention at a in fig. 4.

In the figure: 1-combustion box, 2-feed hopper, 3-elbow, 4-valve, 5-ignition device, 6-buffer plate, 7-first spring, 8-replacement mechanism, 81-flame outlet, 82-ring groove, 83-spray nozzle, 84-square groove, 85-slide block, 86-limit rod, 87-clamping groove, 9-buffer support mechanism, 91-bottom plate, 92-groove, 93-slide plate, 94-rotating rod, 95-sliding groove, 96-moving block, 97-second spring, 98-rotating shaft, 99-support rod and 910-inclined groove.

Detailed Description

The technical solutions in the embodiments of the present invention will be clearly and completely described below with reference to the drawings in the embodiments of the present invention, and it is obvious that the described embodiments are only a part of the embodiments of the present invention, and not all of the embodiments. All other embodiments, which can be derived by a person skilled in the art from the embodiments given herein without making any creative effort, shall fall within the protection scope of the present invention.

Referring to fig. 1-5, the present invention provides a technical solution: a test device for combustion of a solid rocket engine comprises a combustion box 1, wherein a feed hopper 2 is fixedly connected to the left side of the combustion box 1, the bottom of the feed hopper 2 is communicated with an elbow 3, the right end of the elbow 3 penetrates through the combustion box 1 and extends into the combustion box 1, a valve 4 is arranged inside the elbow 3, the valve 4 can control the inflow of fuel, when the valve 4 is closed, the gas inside the combustion box 1 can only be sprayed out through a flame outlet 81, an ignition device 5 is arranged on the front side of the combustion box 1, the ignition device 5 is the prior art and can ignite and combust propellant fuel inside the combustion box 1 and is controlled by an external switch, four buffer plates 6 are slidably connected to the front side, the rear side, the left side and the right side of the bottom of the inner wall of the combustion box 1, first springs 7 are fixedly connected between the sides, away from the four buffer plates 6, the right end of the elbow 3 penetrates through the left buffer plate 6 and extends to the right side of the buffer plates 6, the outer surface of the elbow 3 is connected with the inner surface of the buffer plate 6 in a sliding way, and the top of the combustion box 1 is provided with a replacement mechanism 8; the replacement mechanism 8 comprises a flame outlet 81 arranged at the top of the combustion box 1, a ring groove 82 is arranged at the top of the combustion box 1 and positioned at the periphery of the flame outlet 81, a spray nozzle 83 is movably connected at the top of the combustion box 1, the bottom of the spray nozzle 83 penetrates through the ring groove 82 and extends into the ring groove 82, square grooves 84 are respectively arranged at the top of the combustion box 1 and positioned at the front side and the rear side of the ring groove 82, sliding blocks 85 are respectively connected on the inner surfaces of the two square grooves 84 in a sliding manner, limiting rods 86 are respectively fixedly connected on the opposite sides of the two sliding blocks 85, clamping grooves 87 are respectively arranged at the front side and the rear side of the spray nozzle 83, the opposite ends of the two limiting rods 86 penetrate through the ring groove 82 and extend into the clamping grooves 87, the outer surfaces of the two limiting rods 86 are respectively clamped with the inner surfaces of the clamping grooves 87, the outer surfaces of the two limiting rods 86 are respectively connected with the inner surfaces of the combustion box 1 in a sliding manner, a buffering support mechanism 9 is arranged at the bottom of the combustion box 1, the buffer supporting mechanism 9 comprises a bottom plate 91 arranged at the bottom of the combustion box 1, a groove 92 is formed in the top of the bottom plate 91, a sliding plate 93 is connected between the inner walls of the groove 92 in a sliding manner, the bottom of the combustion box 1 penetrates through the groove 92 and extends into the groove 92, the bottom of the combustion box 1 is contacted with the top of the sliding plate 93, rotating rods 94 are rotatably connected to the left and right sides of the bottom of the inner wall of the groove 92, a sliding groove 95 is formed in the bottom of the sliding plate 93, moving blocks 96 are slidably connected to the left and right sides of the inner surface of the sliding groove 95, the bottoms of the two moving blocks 96 are rotatably connected with the top end of the rotating rod 94, a second spring 97 is fixedly connected between the far side of the two rotating rods 94 and the bottom of the inner wall of the groove 92, supporting rods 99 are rotatably connected to the left and right sides of the top of the bottom plate 91 through rotating shafts 98, inclined grooves 910 are formed in the left and right sides of the combustion box 1, and the top ends of the two supporting rods 99 penetrate through the inclined grooves 910 and extend into the inclined grooves 910, the two inclined slots 910 have a size slightly larger than that of the support bar 99.

And those not described in detail in this specification are well within the skill of those in the art.

When the fuel injection device works, propellant fuel is poured into the feed hopper 2, meanwhile the propellant fuel enters the combustion box 1 through the bent pipe 3, the ignition device 5 is further started to ignite and combust the fuel in the combustion box 1, heat energy and air flow generated during combustion are discharged through the injection nozzle 83, when the injection nozzle 83 needs to be replaced, the two sliding blocks 85 are made to slide back to back through the two sliding blocks 85, the two sliding blocks 85 drive the limiting rods 86 to slide back, finally the two limiting rods 86 are made to slide away from the clamping grooves 87, the injection nozzle 83 is further lifted upwards, the disassembly of the injection nozzle 83 is completed, when the injection nozzle 83 is installed, the injection nozzle 83 is inserted into the annular groove 82, the two sliding blocks 85 are further pushed, the two limiting rods 86 are driven by the sliding blocks 85 to slide into the clamping grooves 87, the installation and the fixation of the injection nozzle 83 are realized, the quick disassembly and assembly of the injection nozzle 83 are realized through the arrangement of the replacement mechanism 8, and the working efficiency is improved, and the operation is simple and convenient, the practicability is strong, when the combustion box 1 is internally combusted, huge pressure gas is instantly generated in the combustion box 1, the gas extrudes the four buffer plates 6, the four buffer plates 6 begin to extrude and compress the first spring 7, and the arrangement of the buffer plates 6 and the first spring 7 avoids the damage to the inner wall of the combustion box 1 caused by the huge pressure extrusion instantly generated during the combustion, thereby prolonging the service life of the combustion box 1, by rotating the support rod 99 to the inside of the chute 910, when the combustion box 1 is internally combusted, the generated left and right forces can extrude the sliding plate 93, the sliding plate 93 begins to downwards extrude the moving block 96 and the rotating rod 94, the rotating rod 94 begins to compress the second spring 97, the instant extrusion force of the combustion box 1 to the bottom plate 91 is reduced by the arrangement of the buffer supporting mechanism 9, the service life of the bottom plate 91 is prolonged, when the combustion box 1 shakes left and right, the supporting rod 99 moves up and down in a small range inside the chute 910, and meanwhile, the supporting rod 99 can support and protect the combustion box 1, so that the safety is enhanced.

It is noted that, herein, relational terms such as first and second, and the like may be used solely to distinguish one entity or action from another entity or action without necessarily requiring or implying any actual such relationship or order between such entities or actions. Also, the terms "comprises," "comprising," or any other variation thereof, are intended to cover a non-exclusive inclusion, such that a process, method, article, or apparatus that comprises a list of elements does not include only those elements but may include other elements not expressly listed or inherent to such process, method, article, or apparatus.

Although embodiments of the present invention have been shown and described, it will be appreciated by those skilled in the art that changes, modifications, substitutions and alterations can be made in these embodiments without departing from the principles and spirit of the invention, the scope of which is defined in the appended claims and their equivalents.