CN202935577U - Rotor wing protection framework device - Google Patents
Rotor wing protection framework device Download PDFInfo
- Publication number
- CN202935577U CN202935577U CN 201220542440 CN201220542440U CN202935577U CN 202935577 U CN202935577 U CN 202935577U CN 201220542440 CN201220542440 CN 201220542440 CN 201220542440 U CN201220542440 U CN 201220542440U CN 202935577 U CN202935577 U CN 202935577U
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- CN
- China
- Prior art keywords
- rotor
- parachute
- framework
- rotor wing
- jacking block
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Expired - Fee Related
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Abstract
A rotor wing protection framework device comprises an upper rotor wing, a lower rotor wing and a cabin; a rotor wing protection framework is arranged on the outer side of the upper rotor wing and the lower rotor wing and comprises a protection framework and an inclined plane reinforcing framework; the inclined plane reinforcing framework is fixed on the upper side of the cabin; a top block is arranged at the upper end of the protection framework, a parachute box is arranged on the top block, a parachute is arranged in the parachute box, and a parachute cord is arranged on the parachute and is connected to the top block; a spring is further arranged on the top block; when the parachute is folded in the parachute box, the parachute is pressed on the spring; the top block is in coupling connection with a transmission shaft of the upper rotor wing of an aircraft; and a movable cover is connected to the parachute box. The rotor wing protection framework device has the advantages that the movable cover can be automatically opened under the circumstance that the aircraft lose power and the rotor wings are in reverse running, the parachute can be ejected under the action of the spring, and the aircraft can be forced to land on the ground in a safer manner.
Description
Technical field
The utility model relates to a kind of rotor craft, especially relates to a kind of rotor and protects frame mounting.
Background technology
Existing rotor craft does not arrange rotor and protects framework, and parachute can not be installed, and piggyback pod is arranged on the top in cabin, and the center of gravity of aircraft is all in the upper end of aircraft, somewhat top-heavy like this, although its manoevreability is good, it is safe not.Structure is also very complicated, has so just improved technical requirements and the material requirement of its manufacture, and the difficulty of operation and maintenance and cost also increase greatly.
Summary of the invention
Technical problem to be solved in the utility model be to provide a kind of simple in structure, vertical stability good, when forced landing safety and stability a kind of rotor protect frame mounting.
The utility model solves the problems of the technologies described above adopted technical scheme; A kind of rotor protects frame mounting, comprise rotor, lower rotor and cabin, it is characterized in that described upper rotor and described lower rotor arranged outside have rotor to protect framework, described rotor protects framework by protecting framework and the inclined-plane hog frame forms, and described inclined-plane hog frame is fixed on the upside in described cabin.
The described upper end of protecting framework is provided with jacking block, be provided with the umbrella box on described jacking block, be provided with parachute in described umbrella box, be provided with the umbrella rope on described parachute, described umbrella rope is connected on described jacking block, also be provided with spring on described jacking block, described parachute is pressed on described spring while being folded in the umbrella box.
On described jacking block and aircraft, the transmission shaft of rotor is coupling, and on described umbrella box, is provided with removable cover, and described removable cover, under aircraft runs out of steam situation, is opened during the rotor reversing automatically.
Described cabin is arranged with piggyback pod, in described piggyback pod, is provided with variable-speed conversion device, and described variable-speed conversion device is connected with driving engine, also is provided with auxiliary propulsion plant and fuel tank in described piggyback pod.
Described piggyback pod lower end is provided with the connection matrix, on described connection matrix, is connected with a plurality of foot rests, is provided with the Telescopic buffer device on described foot rest, and described foot rest lower end is provided with cardan wheel.
Compared with prior art, the utility model is arranged on the piggyback pod of aircraft weight maximum under cabin, although increased the propeller shaft length between rotor and piggyback pod, but can make like this vertical stability of coaxial aircraft better, rotor is provided with rotor outward and protects frame mounting, protects on framework and is provided with parachute, makes like this aircraft run out of steam in situation, automatic spring parachute during the rotor reversing, the safety that has improved aircraft.
The accompanying drawing explanation
Fig. 1 is constructional drawing of the present utility model;
Fig. 2 is part-structure figure of the present utility model ();
Fig. 3 is part-structure figure of the present utility model (two);
Fig. 4 is part-structure figure of the present utility model (three).
The specific embodiment
Below in conjunction with accompanying drawing, embodiment is described in further detail the utility model.
A kind of rotor protects frame mounting, comprises rotor 11, lower rotor 12 and cabin 3, and upper rotor 11 and lower rotor 12 arranged outside have rotor to protect framework, and rotor protects framework by protecting framework 70 and inclined-plane hog frame 71 forms, and inclined-plane hog frame 71 is fixed on the upside in cabin 3.
The upper end of protecting framework 70 is provided with jacking block 72, is provided with umbrella box 75 on jacking block 72, is provided with parachute 78 in umbrella box 75, be provided with umbrella rope 76 on parachute 78, umbrella rope 76 is connected on jacking block 72, also is provided with spring 77 on jacking block 72, and parachute 78 is pressed on spring 77 while being folded in umbrella box 75.
On jacking block 72 and aircraft, the transmission shaft 47 of rotor 11 is coupling, and being provided with removable cover 73,74 on umbrella box 75 is point of connection, removable cover 73 is under aircraft runs out of steam situation, during the rotor reversing, automatically open, parachute 78 ejects under the effect of spring 77, can implement safe forced landing like this.
Piggyback pod 4 lower ends are provided with and connect matrix 54, connect on matrix 54 and are connected with a plurality of foot rests 52, are provided with Telescopic buffer device 51 on foot rest 52, and foot rest 52 lower ends are provided with cardan wheel 53.
Claims (5)
1. a rotor protects frame mounting, comprise rotor, lower rotor and cabin, it is characterized in that described upper rotor and described lower rotor arranged outside have rotor to protect framework, described rotor protects framework by protecting framework and the inclined-plane hog frame forms, and described inclined-plane hog frame is fixed on the upside in described cabin.
2. a kind of rotor according to claim 1 protects frame mounting, it is characterized in that the described upper end of protecting framework is provided with jacking block, be provided with the umbrella box on described jacking block, be provided with parachute in described umbrella box, be provided with the umbrella rope on described parachute, described umbrella rope is connected on described jacking block, also is provided with spring on described jacking block, and described parachute is pressed on described spring while being folded in the umbrella box.
3. a kind of rotor according to claim 1 protects frame mounting, the transmission shaft that it is characterized in that rotor on described jacking block and aircraft is coupling, be provided with removable cover on described umbrella box, described removable cover, under aircraft runs out of steam situation, is opened during the rotor reversing automatically.
4. a kind of rotor according to claim 1 protects frame mounting, it is characterized in that described cabin is arranged with piggyback pod, be provided with variable-speed conversion device in described piggyback pod, described variable-speed conversion device is connected with driving engine, also is provided with auxiliary propulsion plant and fuel tank in described piggyback pod.
5. a kind of rotor according to claim 4 protects frame mounting, it is characterized in that described piggyback pod lower end is provided with the connection matrix, be connected with a plurality of foot rests on described connection matrix, be provided with the Telescopic buffer device on described foot rest, described foot rest lower end is provided with cardan wheel.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN 201220542440 CN202935577U (en) | 2012-10-23 | 2012-10-23 | Rotor wing protection framework device |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN 201220542440 CN202935577U (en) | 2012-10-23 | 2012-10-23 | Rotor wing protection framework device |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN202935577U true CN202935577U (en) | 2013-05-15 |
Family
ID=48319831
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN 201220542440 Expired - Fee Related CN202935577U (en) | 2012-10-23 | 2012-10-23 | Rotor wing protection framework device |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN202935577U (en) |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN105329451A (en) * | 2015-01-04 | 2016-02-17 | 北京零零无限科技有限公司 | Full protection unmanned aerial vehicle |
-
2012
- 2012-10-23 CN CN 201220542440 patent/CN202935577U/en not_active Expired - Fee Related
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN105329451A (en) * | 2015-01-04 | 2016-02-17 | 北京零零无限科技有限公司 | Full protection unmanned aerial vehicle |
| US10035589B2 (en) | 2015-01-04 | 2018-07-31 | Beijing Zero Zero Infinity Technology Co., Ltd | Foldable drone |
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Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| C14 | Grant of patent or utility model | ||
| GR01 | Patent grant | ||
| C17 | Cessation of patent right | ||
| CF01 | Termination of patent right due to non-payment of annual fee |
Granted publication date: 20130515 Termination date: 20131023 |