CN104326094A - Jet transfer device - Google Patents
Jet transfer device Download PDFInfo
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- CN104326094A CN104326094A CN201410453262.3A CN201410453262A CN104326094A CN 104326094 A CN104326094 A CN 104326094A CN 201410453262 A CN201410453262 A CN 201410453262A CN 104326094 A CN104326094 A CN 104326094A
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- nozzles
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Abstract
The invention provides a jet transfer device. The device mainly comprises a high-pressure gas source, a gas path pipeline, an electric explosion valve, a high-pressure self-locking valve and a nozzle component, wherein the high-pressure gas source, the electric explosion valve, the high-pressure self-locking valve and the nozzle component are in butt welding joint through the gas path pipeline in sequence; the nozzle component consists of an annular cylinder and a plurality of nozzles which are uniformly distributed on the annular cylinder; each nozzle comprises an inlet straight section, a streamline contraction section and an outlet straight section; the length ratio of the inlet straight section and the outlet straight section is 3:1; the contraction angle of the streamline contraction section is 7.63 degrees; the inlet diameter of the inlet straight section is phi 4 mm; the outlet diameter of the outlet straight section is phi 2 mm. The nozzles in the nozzle component are streamline contraction type nozzles, and the sizes of the inlet straight sections, the streamline contraction sections and the outlet straight sections of the nozzles are designed respectively, so that the net thrust of the nozzles is excellently increased, and the transfer stroke of a transferred object is increased.
Description
Technical field
The present invention relates to a kind of jet transfer device, belong to aircraft spacecrafts rendezvous technical field.
Background technology
Spacecrafts rendezvous mechanism is the key mechanism that two aircraft realize rigid attachment, docking technique common at present has: " rod-cone " docking system, " homologous perimetric pattern " docking system, " capture type " docking system etc., these docking mechanisms are using mechanical energy as power, complex structure, volume is large, and merging precision requires higher.
Summary of the invention
In view of this, the object of this invention is to provide a kind of jet transfer device, this apparatus structure is simple, and power obtains easily, can obtain the transfer power output of different size by controlling jet time, for docking transfer provides a kind of method easily and effectively.
Technical solution of the present invention is to achieve these goals:
A kind of jet transfer device, this device forms primarily of high-pressure air source, gas path pipe, electric blasting valve, high pressure latching valve and nozzle assembly; Wherein high-pressure air source, electric blasting valve, high pressure latching valve and nozzle assembly carry out butt welding connection by gas path pipe successively; Described nozzle assembly is made up of circular cylinder and the multiple nozzles be distributed on circular cylinder, wherein said nozzle comprises entrance linear portion, streamline contraction section and outlet linear portion, the length of inlet line section and outlet linear portion is than being 3:1, the angle of throat of streamline contraction section is 7.63 °, and the eye diameter of inlet line section is Φ 4mm, the outlet diameter of outlet linear portion is Φ 2mm.
Further, when jet transfer device of the present invention is applied in two aircraft spacecrafts rendezvous, described high-pressure air source is the high pressure gas in aircraft gas cylinder.
Beneficial effect
Nozzle in nozzle assembly of the present invention adopts streamline shrinkage type nozzle, and designs the size of the inlet line section of nozzle, streamline contraction section and outlet linear portion respectively, increases the net thrust of nozzle well, increases the transfer stroke of transfer.
The jet transfer device of the present invention is being applied in two aircraft (recoverable capsule and lifting device) spacecrafts rendezvous, utilizes residual high pressure gas in lifting device gas cylinder to be pushed to recoverable capsule sampling receptacle cabin in by object to be transferred from initial position lifting device as high-pressure air source; Therefore the jet transfer device of the present invention is without the need to separately establishing high-pressure air source, and it has, and structure is simple, and volume is little, and power such as easily to obtain at the feature.
Accompanying drawing explanation
Fig. 1 is the constructional drawing of jet transfer device;
Fig. 2 is the constructional drawing of nozzle;
In figure: 1 high-pressure air source, 2 electric blasting valves, 3 high pressure latching valves, 4 gas path pipes, 5 nozzle assemblies.
Detailed description of the invention
Below in conjunction with the drawings and specific embodiments, the present invention will be further described.
As shown in Figure 1, a kind of jet transfer device of the present invention, this device forms primarily of high-pressure air source 1, gas path pipe 4, electric blasting valve 2, high pressure latching valve 3 and nozzle assembly 5; Annexation is: high-pressure air source 1, electric blasting valve 2, high pressure latching valve 3 and nozzle assembly 5 carry out butt welding connection by gas path pipe 4 successively; Wherein said nozzle assembly is made up of circular cylinder and the multiple nozzles be distributed on circular cylinder; Described nozzle comprises entrance linear portion A, streamline contraction section B and outlet linear portion C, wherein the length of inlet line section A and outlet linear portion C is than being 3:1, the angle of throat of streamline contraction section B is 7.63 °, and the eye diameter of inlet line section A is Φ 4mm, the outlet diameter of outlet linear portion C is Φ 2mm.
Nozzle in nozzle assembly is the element of high pressure gas transformation of energy, and be again the direct element forming jet operating mode, the quality of its performance will directly affect the success or failure of jet transfer.Consider the pressure drop and resistance that reduce nozzle interior, increase the pressure of jet expansion, slow down the decay of ejection air-flow, the present invention devises streamline shrinkage type nozzle (as shown in Figure 2), nozzle of the present invention comprises entrance linear portion A, streamline contraction section B and outlet linear portion C, employing computational fluid dynamics is simulated, and the length determining inlet line section A and outlet linear portion C is 7.63 ° than the angle of throat for 3:1, streamline contraction section B; Other design results in contrast design, demonstrate the validity of this method of designing.Simultaneously carry out the performance analysis of jet pipe according to design conditions, compared for the flow field of jet pipe in the situations such as boundary layer correction, constant specific heat/variable specific heat, jet pipe gangway angle of attack variation, and carried out performance analysis.Known, compared with straight wall configuration, streamline shrinkage type jet pipe internal resistance increases 15%, and net thrust increases 22%; Compared with the 3-d modelling generated based on Maximum Thrust Nozzle, streamline shrinkage type nozzle thrust reduces 5%, and shifts stroke increase 20%.Final is 4.5MPa at high-pressure air source 1 pressure, and in nozzle assembly 5, streamline shrinkage type jet pipe is at nozzle outlet diameter Φ 2mm, nozzle entrance diameter of phi 4mm, can export the thrust of 40N and the transfer stroke of 600mm when angle of throat is 7.63 °.
High pressure latching valve 3 of the present invention adopts double containment plunger connector; Simultaneously in order to bear the mechanical environment in flight course, electric blasting valve 2 is fixed on structural slab by the screw of 4 M5, and nozzle assembly and pipeline assembly are fixed on structural slab by support.
The jet transfer device of the present invention is being applied in two aircraft (recoverable capsule and lifting device) spacecrafts rendezvous, utilizes residual high pressure gas in lifting device gas cylinder to be pushed to recoverable capsule sampling receptacle cabin in by object to be transferred from initial position lifting device as high-pressure air source; Now the principle of work of jet transfer device is:
Electric blasting valve 2 controls the break-make of gas circuit, and high pressure latching valve 3 controls the time of jet output.In the lunar oribt, electric blasting valve 2 and high pressure latching valve 3 are in normally off, and gas circuit is not communicated with, and prevents Leakage Gas, and now jet transfer device does not carry out mating operation.When providing priming supply for sub power distribution system, operating voltage is 23 ~ 29V, and now electric blasting valve is ignited, air path part is communicated with, and high pressure gas arrive high pressure latching valve 3 through electric blasting valve 2 from lifting device gas cylinder, and now high pressure latching valve 3 does not work, gas circuit is not communicated with, and device does not work.When advancing circuit box provides valve electric current, working current is 3.5A, Low level effective; Now high pressure latching valve 3 valve opening, so far gas circuit is all communicated with.High pressure gas arrive nozzle place through high pressure latching valve 3, and device is started working.When device is started working, high pressure draft sprays through nozzle, and airflow function is in the bottom of object to be transferred, and to object to be transferred initial motion energy, then object to be transferred moves by force of inertia, completes transfer process.This device is when bleed pressure 4.5MPa, and adjustment nozzle arrangements, reaches thrust large, the object that stroke is far away
In sum, these are only preferred embodiment of the present invention, be not intended to limit protection scope of the present invention.Within the spirit and principles in the present invention all, any amendment done, equivalent replacement, improvement etc., all should be included within protection scope of the present invention.
Claims (2)
1. a jet transfer device, this device forms primarily of high-pressure air source, gas path pipe, electric blasting valve, high pressure latching valve and nozzle assembly; Wherein high-pressure air source, electric blasting valve, high pressure latching valve and nozzle assembly carry out butt welding connection by gas path pipe successively; It is characterized in that, described nozzle assembly is made up of circular cylinder and the multiple nozzles be distributed on circular cylinder, wherein said nozzle comprises entrance linear portion, streamline contraction section and outlet linear portion, the length of inlet line section and outlet linear portion is than being 3:1, the angle of throat of streamline contraction section is 7.63 °, and the eye diameter of inlet line section is Φ 4mm, the outlet diameter of outlet linear portion is Φ 2mm.
2. jet transfer device according to claim 1, it is characterized in that, when described jet transfer device is applied in two aircraft spacecrafts rendezvous, described high-pressure air source is the high pressure gas in aircraft gas cylinder.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201410453262.3A CN104326094A (en) | 2014-09-05 | 2014-09-05 | Jet transfer device |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201410453262.3A CN104326094A (en) | 2014-09-05 | 2014-09-05 | Jet transfer device |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN104326094A true CN104326094A (en) | 2015-02-04 |
Family
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Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201410453262.3A Pending CN104326094A (en) | 2014-09-05 | 2014-09-05 | Jet transfer device |
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Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US3471106A (en) * | 1965-05-28 | 1969-10-07 | Rocket Research Corp | Valveless microrocket systems |
| JPH03204400A (en) * | 1990-01-08 | 1991-09-05 | Mitsubishi Electric Corp | Attitude orbit control thruster |
| JPH05170193A (en) * | 1991-12-25 | 1993-07-09 | Mitsubishi Heavy Ind Ltd | Thrust direction-variable thruster |
| JPH0624398A (en) * | 1992-07-07 | 1994-02-01 | Mitsubishi Heavy Ind Ltd | Spin imparting device for spacecraft and the like |
| CN1206671A (en) * | 1997-07-25 | 1999-02-03 | 航空发动机的结构和研究公司 | Compact single propelling agent unit prepelling system for small artificial satellite |
| CN102926889A (en) * | 2012-10-31 | 2013-02-13 | 北京控制工程研究所 | Method for using bipropellants efficiently |
-
2014
- 2014-09-05 CN CN201410453262.3A patent/CN104326094A/en active Pending
Patent Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US3471106A (en) * | 1965-05-28 | 1969-10-07 | Rocket Research Corp | Valveless microrocket systems |
| JPH03204400A (en) * | 1990-01-08 | 1991-09-05 | Mitsubishi Electric Corp | Attitude orbit control thruster |
| JPH05170193A (en) * | 1991-12-25 | 1993-07-09 | Mitsubishi Heavy Ind Ltd | Thrust direction-variable thruster |
| JPH0624398A (en) * | 1992-07-07 | 1994-02-01 | Mitsubishi Heavy Ind Ltd | Spin imparting device for spacecraft and the like |
| CN1206671A (en) * | 1997-07-25 | 1999-02-03 | 航空发动机的结构和研究公司 | Compact single propelling agent unit prepelling system for small artificial satellite |
| CN102926889A (en) * | 2012-10-31 | 2013-02-13 | 北京控制工程研究所 | Method for using bipropellants efficiently |
Non-Patent Citations (1)
| Title |
|---|
| 杨国来等: "锥直形喷嘴内部结构参数对射流流场影响的数值模拟", 《液压与气动》 * |
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Application publication date: 20150204 |