CN202686772U - Unmanned aerial vehicle ejection system capable of being extended and retracted rapidly - Google Patents
Unmanned aerial vehicle ejection system capable of being extended and retracted rapidly Download PDFInfo
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- CN202686772U CN202686772U CN 201220148127 CN201220148127U CN202686772U CN 202686772 U CN202686772 U CN 202686772U CN 201220148127 CN201220148127 CN 201220148127 CN 201220148127 U CN201220148127 U CN 201220148127U CN 202686772 U CN202686772 U CN 202686772U
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- ejection
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- ejection orbit
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Abstract
The utility model relates to an ejection system and particularly relates to an unmanned aerial vehicle ejection system capable of being extended and retracted rapidly. The system comprises a strip-shaped rail, wherein a short supporting leg is arranged in an initial section of the rail, a long supporting leg is arranged in a tail section of the rail, and both the short supporting leg and the long supporting leg have an extending state and a retracting state. The system has the advantages of being simple in structure, small in size, light in weight, high in intensity, reliable to use, low in cost, high in reusability and particularly suitable for carrying in a single-man rucksack.
Description
Technical field
This novel ejection system that belongs to, but be specifically related to the unmanned aerial vehicle ejecting system of a kind of rapid deployment/recovery.
Background technology
Unmanned plane is a kind of small unmanned vehicles, can be by remote control or autonomous flight.Existing unmanned aerial vehicle ejecting mode adopts that mainly hydraulic catapult, Pneumatic ejection, electromagnetic launch and elastic body launch etc., the problem such as wherein hydraulic pressure, air pressure, electromagnetic launch all exist complex structure, involve great expense, manoevreability is poor, elastic body launches then because structure is relatively simple the aspects such as and SUAV (small unmanned aerial vehicle) relatively low in emission rate and is widely used, but the elastic body ejection mode is too because the problem of launching trajectory length exists the large shortcoming that takes up room, therefore generally will be designed to folding ejection system, but general fold mechanism is complicated, weight is bigger than normal.
Summary of the invention
The utility model is for the defective of prior art, but the unmanned aerial vehicle ejecting system of a kind of rapid deployment/recovery is provided.
Summary of the invention: but the unmanned aerial vehicle ejecting system of a kind of rapid deployment/recovery comprises the track of strip, is provided with short supporting leg at the initial segment of track, is provided with long leg at the latter end of track, and two states is all opened/regained to described short supporting leg and long leg.
But the unmanned aerial vehicle ejecting system of aforesaid a kind of rapid deployment/recovery wherein, arranges several interludes between latter end and initial segment.
But the unmanned aerial vehicle ejecting system of aforesaid a kind of rapid deployment/recovery, wherein, the initial segment of ejection system comprises ejection orbit, this ejection orbit cooperates the track that forms ejection system with miscellaneous part, end at ejection orbit is provided with rotating shaft, described short supporting leg is arranged in this rotating shaft, and fix with locating dowel pin, the other end at ejection orbit is provided with exchanging structure spare, this exchanging structure spare is the structure part identical with ejection orbit, be used for ejection orbit and be connected with other parts, limiting stopper also is set on ejection orbit, limiting stopper is used for cooperating exchanging structure spare to guarantee to connect more fastening.
But the unmanned aerial vehicle ejecting system of aforesaid a kind of rapid deployment/recovery, wherein, the latter end of ejection system comprises ejection orbit, this ejection orbit cooperates the track that forms ejection system with miscellaneous part, be provided with spacing knob in the end of ejection orbit, fixed length supporting leg on the spacing knob also arranges limiting stopper on ejection orbit.
But the unmanned aerial vehicle ejecting system of aforesaid a kind of rapid deployment/recovery, wherein, interlude comprises ejection orbit, is provided with exchanging structure spare at an end of ejection orbit, and limiting stopper also is set on ejection orbit.
Effect of the present utility model is: this ejection system is simple in structure, volume is little, lightweight, intensity is high, use is reliable, cost is low, reusability is strong, be particularly suitable for single knapsack and carry.
Description of drawings
Ejection system after Fig. 1 launches fully;
Fig. 2 initial segment module;
Fig. 3 interlude module;
Fig. 4 latter end module;
Initial segment module after the short supporting leg of Fig. 5 is folding;
Fig. 6 removes the latter end module after the long leg;
Fig. 7 exchanging structure spare;
Fig. 8 module connects rear defence and throws off design.
Among the figure: 1. exchanging structure spare, 2. ejection orbit, 3. limiting stopper, 4. lack supporting leg, 5. locating dowel pin, 6. rotating shaft, 7. long leg, 8. spacing knob, 9. spring buckle.
The specific embodiment
Below in conjunction with drawings and Examples to this novel being described further.
As shown in Figure 1, but the unmanned aerial vehicle ejecting system of a kind of rapid deployment/recovery comprises the track of strip, is provided with short supporting leg 4 at the initial segment of track, is provided with long leg 7 at the latter end of track.Two states is all opened/regained to described short supporting leg 4 and long leg 7.When short supporting leg 4 and long leg 7 in opened condition the time, the track of ejection system is latter end height, state that initial segment is low; When short supporting leg 4 and long leg 7 were retracted state, short supporting leg 4 and long leg 7 were close to track, and ejection system is strip, were convenient to transportation and stored.
When the length of ejection system can not meet the demands, can in the middle of latter end and initial segment, increase several interludes.
Such as accompanying drawing 2 and shown in Figure 5, the initial segment of ejection system comprises ejection orbit 2, and this ejection orbit 2 cooperates the track that forms ejection system with miscellaneous part.Be provided with rotating shaft 6 in the end of ejection orbit 2, described short supporting leg 4 is arranged in this rotating shaft 6, and fixing with locating dowel pin 5.Short supporting leg 4 after fixing has opens/regains two states.The other end at ejection orbit 2 is provided with exchanging structure spare 1, and this exchanging structure spare 1 is the part that structure and ejection orbit 2 are complementary, and is used for ejection orbit 2 and is connected with other parts.Limiting stopper 3 also is set on ejection orbit 2, and limiting stopper 3 is used for cooperating exchanging structure spare 1 to guarantee to connect more fastening.
Such as Fig. 4 and shown in Figure 6, the latter end of ejection system comprises ejection orbit 2, and this ejection orbit 2 cooperates the track that forms ejection system with miscellaneous part.Be provided with spacing knob 8 in the end of ejection orbit 2, fixed length supporting leg 7 on the spacing knob 8.When long leg 7 was fixed on the spacing knob 8, long leg 7 in opened condition; When long leg 7 was pulled down from spacing knob 8, long leg 7 was retracted state.Long leg 7 can play the track leveling and adjust the effect of angle of divergence.Limiting stopper 3 also is set on ejection orbit 2.
As shown in Figure 3, interlude comprises ejection orbit 2, is provided with exchanging structure spare 1 at an end of ejection orbit 2, and limiting stopper 3 also is set on ejection orbit 2.
As shown in Figure 7, exchanging structure spare 1 is the part of internal diameter and ejection orbit 2 couplings, and its length slightly is longer than the seam of junction ejection orbit 2.Ejection orbit 2 in this example is two and be arranged in parallel that every cross section is U-shaped shaft-like part, and therefore corresponding exchanging structure spare 1 is the part of cross section similar " 8 " type.
As shown in Figure 8, limiting stopper 3 is provided with spring buckle 9, is provided with the groove corresponding with spring buckle 9 at exchanging structure spare 1.When needs connected different part, at first the ejection orbit 2 with different parts was arranged in the exchanging structure spare 1, and then limiting stopper 3 buckles into spring buckle 9 in the groove of exchanging structure spare 1 at last near exchanging structure spare 1, realized connecting.
Claims (5)
1. but the unmanned aerial vehicle ejecting system of rapid deployment/recovery, the track that comprises strip, it is characterized in that: the initial segment at track is provided with short supporting leg (4), latter end at track is provided with long leg (7), and two states is all opened/regained to described short supporting leg (4) and long leg (7).
2. but the unmanned aerial vehicle ejecting system of a kind of rapid deployment as claimed in claim 1/recovery is characterized in that: several interludes are set between latter end and initial segment.
3. but the unmanned aerial vehicle ejecting system of a kind of rapid deployment as claimed in claim 2/recovery, it is characterized in that: the initial segment of ejection system comprises ejection orbit (2), this ejection orbit (2) cooperates the track that forms ejection system with miscellaneous part, be provided with rotating shaft (6) in the end of ejection orbit (2), described short supporting leg (4) is arranged in this rotating shaft (6), and fixing with locating dowel pin (5), the other end at ejection orbit (2) is provided with exchanging structure spare (1), this exchanging structure spare (1) is the structure part identical with ejection orbit (2), being used for ejection orbit (2) is connected with other parts, limiting stopper (3) also is set on ejection orbit (2), and limiting stopper (3) is used for cooperating exchanging structure spare (1) to guarantee to connect more fastening.
4. but the unmanned aerial vehicle ejecting system of a kind of rapid deployment as claimed in claim 3/recovery, it is characterized in that: the latter end of ejection system comprises ejection orbit (2), this ejection orbit (2) cooperates the track that forms ejection system with miscellaneous part, be provided with spacing knob (8) in the end of ejection orbit (2), the upper fixed length supporting leg (7) of spacing knob (8) also arranges limiting stopper (3) on ejection orbit (2).
5. but the unmanned aerial vehicle ejecting system of a kind of rapid deployment as claimed in claim 4/recovery, it is characterized in that: interlude comprises ejection orbit (2), end at ejection orbit (2) is provided with exchanging structure spare (1), and limiting stopper (3) also is set on ejection orbit (2).
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN 201220148127 CN202686772U (en) | 2012-04-10 | 2012-04-10 | Unmanned aerial vehicle ejection system capable of being extended and retracted rapidly |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN 201220148127 CN202686772U (en) | 2012-04-10 | 2012-04-10 | Unmanned aerial vehicle ejection system capable of being extended and retracted rapidly |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN202686772U true CN202686772U (en) | 2013-01-23 |
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Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN 201220148127 Expired - Lifetime CN202686772U (en) | 2012-04-10 | 2012-04-10 | Unmanned aerial vehicle ejection system capable of being extended and retracted rapidly |
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| Country | Link |
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| CN (1) | CN202686772U (en) |
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN103803095A (en) * | 2014-03-03 | 2014-05-21 | 重庆翼动科技有限公司 | Pneumatic launcher for mini-type unmanned plane |
| CN106005466A (en) * | 2016-07-12 | 2016-10-12 | 福建工程学院 | Demountable minitype unmanned plane launching cradle |
-
2012
- 2012-04-10 CN CN 201220148127 patent/CN202686772U/en not_active Expired - Lifetime
Cited By (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN103803095A (en) * | 2014-03-03 | 2014-05-21 | 重庆翼动科技有限公司 | Pneumatic launcher for mini-type unmanned plane |
| CN103803095B (en) * | 2014-03-03 | 2016-05-25 | 重庆翼动科技有限公司 | The Pneumatic catapult of SUAV |
| CN106005466A (en) * | 2016-07-12 | 2016-10-12 | 福建工程学院 | Demountable minitype unmanned plane launching cradle |
| CN106005466B (en) * | 2016-07-12 | 2018-03-30 | 福建工程学院 | A kind of reassembling type SUAV launching cradle |
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| Date | Code | Title | Description |
|---|---|---|---|
| C14 | Grant of patent or utility model | ||
| GR01 | Patent grant | ||
| CX01 | Expiry of patent term |
Granted publication date: 20130123 |
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| CX01 | Expiry of patent term |