CN103105102A - Buffering and driving system of missile folding mechanism - Google Patents
Buffering and driving system of missile folding mechanism Download PDFInfo
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- CN103105102A CN103105102A CN2012105269674A CN201210526967A CN103105102A CN 103105102 A CN103105102 A CN 103105102A CN 2012105269674 A CN2012105269674 A CN 2012105269674A CN 201210526967 A CN201210526967 A CN 201210526967A CN 103105102 A CN103105102 A CN 103105102A
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- piston
- buffering
- powder column
- pressurized strut
- actuator cylinder
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Abstract
The invention relates to a buffering and driving system of a missile folding mechanism. The buffering and driving system of the missile folding mechanism comprises an ignition mechanism at one end of an actuator cylinder and a piston in the actuator cylinder and driven by the actuator cylinder. The ignition mechanism comprises a grain in the actuator cylinder and an electric spark pipe out of the grain, a partition plate is positioned between the grain and the electric spark pipe to separate the grain from the electric spark pipe, and the electric spark pipe ignites the grain. A piston rod is mounted on one end of the piston, and the piston rod stretches out of the other end of the actuator cylinder and is connected with the folding mechanism through a connecting piece. The actuator cylinder is divided into a power cavity and a buffering cavity, a communicating channel parallel to an axis of the actuator cylinder is arranged on an inner wall of the actuator cylinder, one end of the communicating channel is communicated with the power cavity, and the other end of the communicating channel is connected with the buffering cavity. The buffering and driving system of the missile folding mechanism has the advantages that principle is simple, moving speed of the piston can be controlled, buffering effect is achieved, sufficient power output is guaranteed, and the system is capable of meeting buffering technology demand of various missile folding mechanisms.
Description
Technical field
The present invention relates to guided missile drives structure design field, specifically, relate to a kind of Missile Folding mechanism buffering drive system.
Background technology
For satisfying the fold mechanism design needs such as Missile Folding missile wing, folding fin, folded antenna, require the fold mechanism drive system to have the function of driving and guarantee that mechanism reliably switches, requirement has pooling feature assurance structural member and electronic devices and components integrality again simultaneously, particularly for outer year large, the labile image of loading direction/instruction antenna class sensitivity electronic devices and components and folding wing/empennage.In general conventional art the power sources such as spring force formula, compressed air active force formula, gaseous-pressure formula can not satisfy simultaneously large load output, buffering effect and small size designing requirement, therefore need a kind of buffering drive system, requirement should guarantee fold mechanism reliable translation-angle, avoid again putting in place impact injury structural member and the responsive electronic devices and components of launching smoothly.
Summary of the invention
The object of the invention is to overcome the deficiencies in the prior art, adapt to reality needs, provide a kind of Missile Folding mechanism to cushion drive system.
In order to realize purpose of the present invention, the technical solution used in the present invention is:
a kind of Missile Folding mechanism buffering drive system, comprise the ignition mechanism that is positioned at pressurized strut one end and be positioned at pressurized strut by the piston of igniting gas driven, ignition mechanism comprises the powder column that is positioned at pressurized strut and is positioned at the electrical discharge tube of powder column outer end, separate by the dividing plate between being located at both between described powder column and electrical discharge tube, electrical discharge tube is lighted powder column, described piston one side is provided with piston rod and piston rod and is connected with fold mechanism by connecting portion after the other end of pressurized strut stretches out, the internal cavity of described pressurized strut is divided into power cavity and cushion chamber by piston, the barrel inside of described pressurized strut also is provided with the communicating passage parallel with the pressurized strut axis, described communicating passage one end is communicated with power cavity, the other end is communicated with cushion chamber.
The connectivity part of described communicating passage and power cavity is provided with the power cavity flow-limiting valve, and the connectivity part of described communicating passage and cushion chamber is provided with the cushion chamber flow-limiting valve.
Described powder column is provided with powder column outward and coats, and described powder column is communicated with communicating passage by the power source flow-limiting valve.
Beneficial effect of the present invention is:
1. should cushion the drive system principle simple, piston movement speed is controlled, has both reached buffering effect, has again abundant power output, can be applicable to the requirement of various Missile Folding mechanism deploying buffer technology;
2. guarantee fold mechanism reliable translation-angle, avoid again putting in place impact injury structural member and the responsive electronic devices and components of launching smoothly;
3. can reach by adjusting each flow-limiting valve the buffering effect of control piston bar movement velocity.
Description of drawings
Fig. 1 is sectional structure schematic diagram of the present invention.
Fig. 2 is the A-A cutaway view of Fig. 1.
The specific embodiment
The present invention is further described below in conjunction with drawings and Examples:
Embodiment: referring to Fig. 1, Fig. 2.
a kind of Missile Folding mechanism buffering drive system, comprise the ignition mechanism that is positioned at pressurized strut one end and be positioned at pressurized strut by the piston 12 of igniting gas driven, seal by sealing ring 3 between the inwall of piston 12 and pressurized strut 10, ignition mechanism comprises the powder column 14 that is positioned at pressurized strut and the electrical discharge tube 8 that is positioned at the powder column outer end, separate by the dividing plate 7 between being located at both between described powder column 14 and electrical discharge tube 8, electrical discharge tube 8 can be lighted powder column 14, described piston 12 1 sides are provided with piston rod 9 and piston rod 9 and are connected with fold mechanism by connecting portion 16 after the other end of pressurized strut 10 stretches out, the internal cavity of described pressurized strut 10 is divided into power cavity 13 and cushion chamber 11 by piston 12, the barrel inside of described pressurized strut 10 also is provided with the communicating passage parallel with the pressurized strut axis 2, described communicating passage 2 one ends are communicated with power cavity 13, the other end is communicated with cushion chamber 11.
Described communicating passage 2 is provided with power cavity flow-limiting valve 4 with the connectivity part of power cavity 13, and described communicating passage 2 is provided with cushion chamber flow-limiting valve 1 with the connectivity part of cushion chamber 11.
Described powder column is provided with powder column outward and coats 5, and described powder column 14 is communicated with communicating passage 2 by power source flow-limiting valve 6.
Use principle of the present invention is:
After electrical discharge tube 8 is received instruction, the powder column 14 that ignites, the combustion gas multiparity air cavity 15 that powder column 14 burnings produce enters communicating passage 2 by power source flow-limiting valve 6, and enters into power cavity 13 and cushion chamber 11 through power cavity flow-limiting valve 4 and cushion chamber flow-limiting valve 1 respectively.
The realization of thrust output function:
If piston 12 is respectively with the contact area of power cavity 13, cushion chamber 11 gases
,
, because be connected passage 2 of power cavity 13, cushion chamber 11 is communicated with, therefore, the air pressure of two chambers is tending towards equal, simultaneously by
Always have when each cavity gaseous-pressure balance as can be known
, guaranteed that therefore piston rod thrust output function and final piston movement put in place.
The realization of pooling feature:
When piston 12 movement velocitys reach a certain value
The time, power cavity 13 volumes increase rapidly pressure and reduce, and cushion chamber 11 volumes reduce rapidly pressure and increase, and the combustion gas that the combustion gas that flows into power cavity 13 by power cavity flow-limiting valve 4 has little time tonifying Qi and flows out cushion chamber 11 by cushion chamber flow-limiting valve 1 has little time pressure release, at this moment
,
, namely power cavity for the active force of piston 12 less than the active force of cushion chamber for piston 12, piston rod 9 retarded motions (do not consider during analysis outer carry impact), thus play the effect of control piston movement velocity.
The pressure official post increases by the combustion gas that power cavity flow-limiting valve 4 flows into power cavity 13, when piston rod 9 speed drop to a certain value
The time, the combustion gas that flows into power cavities 13 by power cavity flow-limiting valve 4 overcomes and brings pressure change because of the cavity volume change in volume, this moment power cavity 13, cushion chamber 11 pressure
,
, piston rod 9 thrust outputs move forward.
As above-mentioned rule, going round and beginning again keeps piston rod 9 with less than a certain speed
Motion, thus the fold mechanism development rate controlled, reach the dual-use function of process buffering and thrust output.
Cushion chamber flow-limiting valve 1, power cavity flow-limiting valve 4 and power source flow-limiting valve 6 are the through hole shape, and the present invention can reach by the aperture that designing and calculating is adjusted each flow-limiting valve the buffering effect of control piston bar movement velocity.
What embodiments of the invention were announced is preferred embodiment, but is not limited to this, those of ordinary skill in the art; very easily according to above-described embodiment, understand spirit of the present invention, and make different amplifications and variation; but only otherwise break away from spirit of the present invention, all in protection scope of the present invention.
Claims (3)
1. Missile Folding mechanism buffering drive system, comprise the ignition mechanism that is positioned at pressurized strut one end and be positioned at pressurized strut by the piston of igniting gas driven, ignition mechanism comprises the powder column that is positioned at pressurized strut and is positioned at the electrical discharge tube of powder column outer end, separate by the dividing plate between being located at both between described powder column and electrical discharge tube, electrical discharge tube is lighted powder column, described piston one side is provided with piston rod and piston rod and is connected with fold mechanism by connecting portion after the other end of pressurized strut stretches out, it is characterized in that: the internal cavity of described pressurized strut is divided into power cavity and cushion chamber by piston, the barrel inside of described pressurized strut also is provided with the communicating passage parallel with the pressurized strut axis, described communicating passage one end is communicated with power cavity, the other end is communicated with cushion chamber.
2. Missile Folding described according to claim mechanism buffering drive system, it is characterized in that: the connectivity part of described communicating passage and power cavity is provided with the power cavity flow-limiting valve, and the connectivity part of described communicating passage and cushion chamber is provided with the cushion chamber flow-limiting valve.
3. Missile Folding described according to claim mechanism buffering drive system, it is characterized in that: described powder column is provided with powder column outward and coats, and described powder column is communicated with communicating passage by the power source flow-limiting valve.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN2012105269674A CN103105102A (en) | 2012-12-10 | 2012-12-10 | Buffering and driving system of missile folding mechanism |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN2012105269674A CN103105102A (en) | 2012-12-10 | 2012-12-10 | Buffering and driving system of missile folding mechanism |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN103105102A true CN103105102A (en) | 2013-05-15 |
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Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN2012105269674A Pending CN103105102A (en) | 2012-12-10 | 2012-12-10 | Buffering and driving system of missile folding mechanism |
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| CN (1) | CN103105102A (en) |
Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN103644782A (en) * | 2013-11-28 | 2014-03-19 | 江西洪都航空工业集团有限责任公司 | Gunpowder actuator unlocking device |
| CN107063615A (en) * | 2017-02-17 | 2017-08-18 | 南京航空航天大学 | A kind of single gravel erosion combustion gas big gun experimental rig |
| CN107436113A (en) * | 2017-03-30 | 2017-12-05 | 内蒙动力机械研究所 | A kind of combustion gas pressurized strut of gas buffer |
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| USH249H (en) * | 1986-10-07 | 1987-04-07 | The United States Of America As Represented By The Secretary Of The Army | Dual rate actuator |
| CN1215453A (en) * | 1996-04-01 | 1999-04-28 | 艾·哈拉斯安全网股份公司 | Pneumatic unlocking and closing apparatus |
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Cited By (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN103644782A (en) * | 2013-11-28 | 2014-03-19 | 江西洪都航空工业集团有限责任公司 | Gunpowder actuator unlocking device |
| CN107063615A (en) * | 2017-02-17 | 2017-08-18 | 南京航空航天大学 | A kind of single gravel erosion combustion gas big gun experimental rig |
| CN107063615B (en) * | 2017-02-17 | 2019-03-01 | 南京航空航天大学 | A kind of single gravel erosion combustion gas big gun experimental rig |
| CN107436113A (en) * | 2017-03-30 | 2017-12-05 | 内蒙动力机械研究所 | A kind of combustion gas pressurized strut of gas buffer |
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Application publication date: 20130515 |