CN214092071U - Cosmic flight equipment engine full-flow test device and cosmic flight equipment engine - Google Patents
Cosmic flight equipment engine full-flow test device and cosmic flight equipment engine Download PDFInfo
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- CN214092071U CN214092071U CN202023281489.4U CN202023281489U CN214092071U CN 214092071 U CN214092071 U CN 214092071U CN 202023281489 U CN202023281489 U CN 202023281489U CN 214092071 U CN214092071 U CN 214092071U
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Abstract
The utility model relates to a space flight equipment engine technical field, concretely relates to space flight equipment engine full current test device and space flight equipment engine. A space flight device engine full flow test apparatus, comprising: the engine nozzle is provided with an expansion section, a cylinder section and a contraction section arranged between the expansion section and the cylinder section; the flow guide structure is arranged at the opening of the expansion section to occupy partial space at the opening and reserve a gas channel; and the supporting structure is connected with the flow guide structure. The utility model provides a simple structure, weight is less, space flight equipment engine full current test device and space flight equipment engine that the cost is lower.
Description
Technical Field
The utility model relates to a space flight equipment engine technical field, concretely relates to space flight equipment engine full current test device and space flight equipment engine.
Background
In order to obtain high specific impulse, the spray pipe of the engine working at high altitude or space adopts a large expansion ratio. If the engine is tested on a ground test bed, the outside is standard atmospheric pressure, the pressure of the airflow in the spray pipe is reduced due to the increase of the expansion area of the spray pipe until the pressure is lower than the outside standard atmospheric pressure, the outside atmosphere enters the expansion part to surround the internal airflow, so that the fuel gas is separated in a certain distance in the outlet of the spray pipe, namely the spray pipe cannot reach full flow. Thus, the oscillating force generated by the separation of the fuel gas can damage the nozzle, so that the engine can not work normally.
The existing solution is to sleeve a diffuser on the skirt of the nozzle, after the engine is ignited and started, the diffuser and the fuel gas are used for injecting, so that the surrounding of the nozzle rapidly reaches the required vacuum degree, and the fuel gas in the nozzle reaches full flow, and the test method is called as full flow test. However, the device used in the test method has a complicated structure because the O-shaped sealing ring, the corrugated pipe, the adapter bracket, the diffuser and other parts are required to be arranged; in addition, the weight of the engine is increased due to the sealing structure at the connecting part of the corrugated pipe and the engine spray pipe outlet. In the prior art, a test method aiming at measuring the vacuum thrust of the rocket engine is also called as a high altitude simulation test, the principle of the test method is approximately the same as that of a full flow test, and the difference is that a large vacuum chamber is built by the method, and the whole rocket engine is arranged in the vacuum chamber. The method also achieves the effect of enabling the gas in the spray pipe to achieve full flow objectively, but the device used in the method is more complex, heavier and higher in cost.
SUMMERY OF THE UTILITY MODEL
Therefore, the to-be-solved technical problem of the utility model lies in overcoming the cosmic flight equipment engine full flow test device among the prior art complicated structure, and weight is great, the higher defect of cost to a simple structure is provided, weight is less, the lower cosmic flight equipment engine full flow test device of cost and cosmic flight equipment engine.
In order to solve the technical problem, the utility model provides a space flight equipment engine full flow test device, include:
the engine nozzle is provided with an expansion section, a cylinder section and a contraction section arranged between the expansion section and the cylinder section;
the flow guide structure is arranged at the opening of the expansion section to occupy partial space at the opening and reserve a gas channel;
and the supporting structure is connected with the flow guide structure.
Optionally, the flow guide structure is conical, a large head end of the flow guide structure is arranged close to the opening of the expansion section, and a small head end of the flow guide structure is arranged close to the contraction section.
Optionally, the large end of the flow guiding structure extends to the outside of the opening of the expansion section.
Optionally, the axis of the flow directing structure is arranged co-linearly with the axis of the engine nozzle.
Optionally, the relationship between the radius of the large head end of the flow guiding structure and the pressure of the combustion chamber satisfies the following formula:
0.00225ε2+0.1165ε－0.555＝p；
ε＝(πR2－πr2)/πr0 2；
wherein p is the pressure of the combustion chamber, and epsilon is the pressure of the fuel after the diversion structure is addedThe ratio of the sectional area of the opening of the expansion section of the engine spray pipe to the sectional area of the throat part of the engine spray pipe, R is the radius of the opening of the expansion section of the engine spray pipe when the flow guide structure is not added, R is the radius of the large head end of the flow guide structure at the opening of the expansion section, and R is the radius of the large head end of the flow guide structure at the opening of the expansion section0Is the throat radius of the engine nozzle.
Optionally, the flow guiding structure is made of a refractory material.
Optionally, one end of the support structure is connected with the large head end of the diversion structure, and the other end is fixed on the ground.
Optionally, the support structure is fixed at the centre of the big head end of the flow directing structure.
Optionally, the support structure is a stent.
Still provide a space flight equipment engine, include space flight equipment engine full flow test device.
The utility model discloses technical scheme has following advantage:
1. the utility model provides a space flight equipment engine full-flow test device, the setting of the opening part water conservancy diversion structure of engine spray tube expansion section has reduced the cross-sectional area here to reduced the expansion ratio of engine spray tube, makeed the gas in the engine spray tube reach the full-flow, whole device simple structure, weight is less, and the cost is lower.
2. The utility model provides a space flight equipment engine full current test device, water conservancy diversion structure are coniform, and the big head end of water conservancy diversion structure is close to the opening setting of expansion section, and little head end is close to the contraction section setting. Therefore, on the basis of ensuring that the fuel gas in the jet pipe of the engine reaches full flow, the flowing of the fuel gas is not blocked, and the engine can normally run.
3. The utility model provides a space flight equipment engine full current test device, water conservancy diversion structure adopt refractory material to make to bear the washing away of space flight equipment engine high temperature air current.
Drawings
In order to more clearly illustrate the embodiments of the present invention or the technical solutions in the prior art, the drawings used in the embodiments or the technical solutions in the prior art will be briefly described below, and it is obvious that the drawings in the following description are some embodiments of the present invention, and for those skilled in the art, other drawings can be obtained according to these drawings without creative efforts.
Fig. 1 is a schematic diagram of the full-flow test device of the engine of the space flight equipment of the present invention.
Description of reference numerals:
1. an engine nozzle; 2. a flow guide structure; 3. a support structure; 4. an expansion section; 5. a cylinder section; 6. a contraction section; 7. an opening; 8. a gas channel; r, radius of an opening of an expansion section of the engine spray pipe when the flow guide structure is not added; r, radius of the large head end of the flow guide structure at the opening of the expansion section; r is0A throat radius of the engine nozzle.
Detailed Description
The technical solution of the present invention will be described clearly and completely with reference to the accompanying drawings, and obviously, the described embodiments are some, but not all embodiments of the present invention. Based on the embodiments in the present invention, all other embodiments obtained by a person skilled in the art without creative work belong to the protection scope of the present invention.
Furthermore, the technical features mentioned in the different embodiments of the invention described below can be combined with each other as long as they do not conflict with each other.
One embodiment of a full-flow test apparatus for a space vehicle engine, as shown in fig. 1, is a launch vehicle engine, and includes an engine nozzle 1, a flow guiding structure 2, and a support structure 3.
The outlet of engine spray pipe 1 is down, has expansion section 4 and circle section 5, and locates contraction section 6 between expansion section 4 and the circle section 5, and expansion section 4, contraction section 6 and circle section 5 integrated processing shaping, expansion section 4 are frustum form, and the hookup location of expansion section 4 and contraction section 6 is the throat.
Specifically, the large end of the flow guide structure 2 is close to and partially extends to the outside of the opening 7 of the expansion section 4, and the small end is close to the contraction section 6, and a certain distance is reserved between the small end and the contraction section 6.
The relationship between the radius of the large head end of the flow guiding structure 2 and the pressure of the combustion chamber satisfies the following formula:
0.00225ε2+0.1165ε－0.555＝p；
ε＝(πR2－πr2)/πr0 2；
wherein p is the pressure of the combustion chamber, epsilon is the ratio of the sectional area of the opening of the expansion section of the engine nozzle after the flow guide structure is added to the sectional area of the throat part of the engine nozzle, R is the radius of the opening of the expansion section of the engine nozzle when the flow guide structure is not added, R is the radius of the large head end of the flow guide structure at the opening of the expansion section, and R is the radius of the large head end of the flow guide structure at the opening of the expansion section0Is the throat radius of the engine nozzle.
For the convenience of test, a supporting structure 3 is connected below the flow guide structure 2. Specifically, one end of the supporting structure 3 is connected with the large end of the flow guide structure 2, and is fixed at the center of the large end of the flow guide structure 2, and the other end is fixed on the ground. The support structure 3 is a stand.
The full-flow test device for the space flight equipment engine comprises a test device body, a test device body and a test device body.
When the gas in the engine nozzle 1 sequentially passes through the cylinder section 5, the contraction section 6 and the expansion section 4, a high specific impulse is obtained, and when the gas meets the flow guide structure 2, the pressure at the position is relatively increased due to the reduction of the expansion area, so that the external gas flow is prevented from entering, full flow is achieved, and the gas is sprayed out from the opening 7.
The full-flow test device can also be used for full-flow tests of engines of other space flight devices such as missiles, spacecrafts and the like.
As an alternative embodiment, the flow guiding structure 2 may also be cylindrical, square cylindrical, etc., as long as it occupies part of the space at the opening 7 of the expansion section 4.
As an alternative embodiment, the flow-guiding structure 2 may also be arranged flush with the opening 7 of the expansion section 4.
It should be understood that the above examples are only for clarity of illustration and are not intended to limit the embodiments. Other variations and modifications will be apparent to persons skilled in the art in light of the above description. And are neither required nor exhaustive of all embodiments. And obvious variations or modifications can be made without departing from the scope of the invention.
Claims (10)
1. A space flight equipment engine full-flow test device, its characterized in that includes:
an engine nozzle (1) having an expansion section (4) and a cylinder section (5), and a contraction section (6) arranged between the expansion section (4) and the cylinder section (5);
the flow guide structure (2) is arranged at the opening (7) of the expansion section (4) to occupy partial space at the opening (7) and reserve a gas channel (8);
a support structure (3) connected with the flow guide structure (2).
2. The full-flow test device for an engine of a space vehicle according to claim 1, wherein the flow guide structure (2) is conical, and the large end of the flow guide structure (2) is disposed near the opening (7) of the expansion section (4) and the small end is disposed near the contraction section (6).
3. The space flight device engine full flow test apparatus according to claim 2, wherein the large end of the flow guiding structure (2) extends to the outside of the opening (7) of the expansion section (4).
4. The space vehicle equipment engine full flow test device according to claim 2, characterized in that the axis of the flow guiding structure (2) is arranged in line with the axis of the engine nozzle (1).
5. The space flight equipment engine full flow test device according to claim 4, characterized in that the relationship between the radius of the large end of the flow guiding structure (2) and the pressure of the combustion chamber satisfies the following formula:
0.00225ε2+0.1165ε-0.555＝p；
ε＝(πR2-πr2)/πr0 2；
wherein p is the pressure of the combustion chamber, epsilon is the ratio of the sectional area of the opening of the expansion section of the engine nozzle after the flow guide structure is added to the sectional area of the throat part of the engine nozzle, R is the radius of the opening of the expansion section of the engine nozzle when the flow guide structure is not added, R is the radius of the large head end of the flow guide structure at the opening of the expansion section, and R is the radius of the large head end of the flow guide structure at the opening of the expansion section0Is the throat radius of the engine nozzle.
6. The full-flow test device for an engine of a space vehicle according to any one of claims 1 to 5, characterized in that the flow-guiding structure (2) is made of a refractory material.
7. Space flight device engine full flow test arrangement according to any of claims 2 to 5, characterised in that the support structure (3) is connected at one end to the large end of the flow guiding structure (2) and at the other end to the ground.
8. The space flight device engine full flow test apparatus according to claim 7, characterized in that the support structure (3) is fixed at the center of the large end of the flow guiding structure (2).
9. The space flight device engine full flow test apparatus according to claim 8, characterized in that the support structure (3) is a bracket.
10. A space vehicle engine comprising the space vehicle engine full flow test apparatus of any one of claims 1-9.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202023281489.4U CN214092071U (en) | 2020-12-29 | 2020-12-29 | Cosmic flight equipment engine full-flow test device and cosmic flight equipment engine |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202023281489.4U CN214092071U (en) | 2020-12-29 | 2020-12-29 | Cosmic flight equipment engine full-flow test device and cosmic flight equipment engine |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN214092071U true CN214092071U (en) | 2021-08-31 |
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| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202023281489.4U Active CN214092071U (en) | 2020-12-29 | 2020-12-29 | Cosmic flight equipment engine full-flow test device and cosmic flight equipment engine |
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| Country | Link |
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| CN (1) | CN214092071U (en) |
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