CN201506464U - Test-used speed reducing mechanism for underground high-speed aircraft - Google Patents
Test-used speed reducing mechanism for underground high-speed aircraft Download PDFInfo
- Publication number
- CN201506464U CN201506464U CN2009201749483U CN200920174948U CN201506464U CN 201506464 U CN201506464 U CN 201506464U CN 2009201749483 U CN2009201749483 U CN 2009201749483U CN 200920174948 U CN200920174948 U CN 200920174948U CN 201506464 U CN201506464 U CN 201506464U
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- speed reducing
- outer sleeve
- speed
- flap
- pin
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Abstract
The utility model relates to a test-used speed reducing mechanism for an underground high-speed aircraft, which comprises an outer sleeve, speed reducing plates, a spring, a pin remover and a pin shaft; a peripheral device adopts a control system; the even number of speed reducing plates are symmetrically distributed on the periphery of the outer sleeve and connected with the outer sleeve through a rotating shaft; a small hole is formed on each speed reducing plate; the pin remover is mounted on the outer sleeve; a movable pin of the pin remover is mounted in the small hole on the lateral surface of each speed reducing plate for fixing the speed reducing plate and connected with the control system; one end of the spring is fixedly connected inside the outer sleeve, and the other end of the spring is connected with the speed reducing plates in a propping manner. After the control system gives an acting signal, the pin remover acts; the movable pin is released from the small hole on the lateral surface of each speed reducing plate, so that the speed reducing plate is not fixedly supported; the speed reducing plates quickly and synchronously expand under the action of frontal resistance of the spring and fluid; and the expanded speed reducing plates generate the resistance to cause the underground aircraft to decelerate.
Description
Technical field
The utility model relates to the test of a kind of underwater high-speed navigation device and uses speed reduction gearing, belongs to a kind of mechanical device structure field.
Background technology
Because underwater high-speed navigation device will have a wide range of applications in future, in the process of research underwater high-speed navigation device, need test by submarine navigation and verify, how reliable recovery high speed aircraft becomes the key technical problem that must consider in process of the test.When using rocket propulsion under water, the speed of underwater high-speed navigation device can reach more than the 100m/s, and is in stabilized conditions.At the navigation latter end, aircraft becomes unpowered inertia motion, moving situation is by the stable instability that becomes, at this moment, aircraft still is under the fair speed, and underwater high-speed navigation device is used to reduce high speed aircraft sub aqua sport speed exactly with speed reduction gearing, shortens underwater high-speed navigation device unsteady motion time and move distance, help safety, reliable recovery underwater high-speed navigation device, thereby obtain test figures.
The utility model content
The utility model provides a kind of underwater high-speed navigation device test speed reduction gearing, and this speed reduction gearing increases resistance under water by launching flap, can effectively reduce the kinematic velocity of underwater high-speed navigation device.
Speed reduction gearing is used in the test of a kind of underwater high-speed navigation device, comprises outer sleeve, flap, and torsion spring, pin drift and rotating shaft, external equipment is control system; Wherein: flap is even-even and symmetrical distribution on the circumference of outer sleeve, flap is connected with outer sleeve by rotating shaft, the flap side has aperture, pin drift is installed on the outer sleeve, simultaneously the movable pin of pin drift is contained in the aperture of flap side and is used for fixing flap, and movable pin links to each other with control system; Torsion spring one end is fixedly connected on outer sleeve inside, and the other end and conflict with flap is connected.
The position that speed reduction gearing is installed is before the power section of aircraft; For guaranteeing the intensity of flap, the thickness of flap is 1: 1 with the width ratio.
Mode of operation: after control system provides actuating signal, the pin drift action, movable pin is deviate from from the aperture of flap side, make flap lose fixed pedestal, flap is rapid synchronous expansion under the effect of torsion spring and fluid head resistance, the flap that launches produces resistance, makes the submarine navigation device reduction of speed.
Beneficial effect:
1. speed reduction gearing can symmetry launch: the flap symmetric arrangement of speed reduction gearing, and can symmetry launch, produce uniform resistance thereby launch the back, after launching, flap expansion process river is in stabilized conditions to keep aircraft.
2. speed reduction gearing can synchronous expansion: the actuating signal of speed reduction gearing is provided synchronously by control system, and flap launches simultaneously, guarantees that aircraft in moderating process, produces the moment of symmetry to aircraft.
Description of drawings
Fig. 1 is a kind of underwater high-speed navigation of the utility model device test speed reduction gearing closure state structural representation;
Fig. 2 is a kind of underwater high-speed navigation of the utility model device test speed reduction gearing closure state structural representation.
Wherein: 1-outer sleeve, 2-flap, 3-torsion spring, 4-pin drift, 5-rotating shaft
The specific embodiment
Below in conjunction with accompanying drawing the utility model is described further
As shown in Figure 1, speed reduction gearing is used in the test of a kind of underwater high-speed navigation device, comprises outer sleeve 1, flap 2,, torsion spring 3, pin drift 4 and rotating shaft 5, external equipment is control system; Wherein: flap 2 is 4 symmetrical distributions on the circumference of outer sleeve, flap 2 is connected with outer sleeve 1 by rotating shaft 5, the flap side has aperture, pin drift 4 is installed on the outer sleeve, simultaneously the movable pin of pin drift is contained in the aperture of flap side and is used for fixing flap 2, and movable pin links to each other with control system; Torsion spring 3 one ends are fixedly connected on outer sleeve 1 inside, and the other end and conflict with flap 2 is connected.
Mode of operation: after control system provides actuating signal, pin drift 4 actions, the movable pin of pin drift 4 is deviate from from the aperture of flap 2 sides, make flap 2 lose fixed pedestal, flap 2 is rapid synchronous expansion under the effect of torsion spring 3 and fluid head resistance, the flap 2 that launches produces resistance, makes the submarine navigation device reduction of speed.
Claims (3)
1. speed reduction gearing is used in underwater high-speed navigation device test, comprises outer sleeve (1), flap (2), and rotating shaft (5), torsion spring (3) and pin drift (4), external equipment is control system; It is characterized in that: flap (2) is even number and symmetrical distribution on the circumference of outer sleeve, flap (2) is connected with outer sleeve (1) by rotating shaft (5), the flap side has aperture, pin drift (4) is installed on the outer sleeve, the movable pin of pin drift (4) is contained in the aperture of flap (2) side, and movable pin links to each other with control system; Torsion spring (3) one ends are fixedly connected on outer sleeve (1) inside, and the other end and conflict with flap (2) is connected.
2. speed reduction gearing is used in a kind of underwater high-speed navigation device as claimed in claim 1 test, and it is characterized in that: the thickness of flap is 1: 1 with the width ratio.
3. speed reduction gearing use in a kind of underwater high-speed navigation device as claimed in claim 1 test, it is characterized in that: the position of speed reduction gearing installation is before the power section of aircraft.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN2009201749483U CN201506464U (en) | 2009-09-30 | 2009-09-30 | Test-used speed reducing mechanism for underground high-speed aircraft |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN2009201749483U CN201506464U (en) | 2009-09-30 | 2009-09-30 | Test-used speed reducing mechanism for underground high-speed aircraft |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN201506464U true CN201506464U (en) | 2010-06-16 |
Family
ID=42467592
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN2009201749483U Expired - Fee Related CN201506464U (en) | 2009-09-30 | 2009-09-30 | Test-used speed reducing mechanism for underground high-speed aircraft |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN201506464U (en) |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN102030093A (en) * | 2009-09-30 | 2011-04-27 | 中国船舶重工集团公司第七一○研究所 | Speed reducing mechanism for testing underwater high-speed aircraft |
-
2009
- 2009-09-30 CN CN2009201749483U patent/CN201506464U/en not_active Expired - Fee Related
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN102030093A (en) * | 2009-09-30 | 2011-04-27 | 中国船舶重工集团公司第七一○研究所 | Speed reducing mechanism for testing underwater high-speed aircraft |
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Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| C14 | Grant of patent or utility model | ||
| GR01 | Patent grant | ||
| CF01 | Termination of patent right due to non-payment of annual fee | ||
| CF01 | Termination of patent right due to non-payment of annual fee |
Granted publication date: 20100616 Termination date: 20170930 |