CN202935578U - Rotor wing protection framework device - Google Patents
Rotor wing protection framework device Download PDFInfo
- Publication number
- CN202935578U CN202935578U CN 201220543881 CN201220543881U CN202935578U CN 202935578 U CN202935578 U CN 202935578U CN 201220543881 CN201220543881 CN 201220543881 CN 201220543881 U CN201220543881 U CN 201220543881U CN 202935578 U CN202935578 U CN 202935578U
- Authority
- CN
- China
- Prior art keywords
- rotor
- parachute
- rotor wing
- jacking block
- framework
- 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
Links
Images
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; 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 like this, and somewhat top-heavy, 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 manufacturing, 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 the technical scheme that adopts, 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, 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 when being folded in the umbrella box, on described jacking block and aircraft, the transmission shaft of rotor is coupling, be provided with removable cover on described umbrella box, described removable cover is under aircraft runs out of steam situation, automatically open during the rotor reversing.
Described cabin is arranged with piggyback pod, is provided with variable-speed conversion device in described piggyback pod, 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, is connected with a plurality of foot rests on described connection matrix, 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 the 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 and is provided with parachute on framework, and aircraft is run out of steam in situation, automatic spring parachute during the rotor reversing, the safety when having improved the aircraft forced landing.
Description of drawings
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
Embodiment is described in further detail the utility model below in conjunction with accompanying drawing.
a kind of rotor protects frame mounting, comprise rotor 11, lower rotor 12 and cabin 3, upper rotor 11 and lower rotor 12 arranged outside have rotor to protect framework, rotor protects framework by protecting framework 70 and inclined-plane hog frame 71 forms, 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, be provided with umbrella box 75 on jacking block 72, be 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 be provided with spring 77 on jacking block 72, parachute 78 is pressed on spring 77 when being folded in umbrella box 75, on jacking block 72 and aircraft, the transmission shaft 47 of rotor 11 is coupling, be provided with removable cover 73 on umbrella box 75, 74 is point of connection, removable cover 73 is under aircraft runs out of steam situation, automatically open during the rotor reversing, 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 to be 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 (3)
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, 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 when being folded in the umbrella box, on described jacking block and aircraft, the transmission shaft of rotor is coupling, be provided with removable cover on described umbrella box, described removable cover is under aircraft runs out of steam situation, automatically open during the rotor reversing.
2. 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.
3. a kind of rotor according to claim 2 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 201220543881 CN202935578U (en) | 2012-10-23 | 2012-10-23 | Rotor wing protection framework device |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN 201220543881 CN202935578U (en) | 2012-10-23 | 2012-10-23 | Rotor wing protection framework device |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN202935578U true CN202935578U (en) | 2013-05-15 |
Family
ID=48319832
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN 201220543881 Expired - Fee Related CN202935578U (en) | 2012-10-23 | 2012-10-23 | Rotor wing protection framework device |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN202935578U (en) |
-
2012
- 2012-10-23 CN CN 201220543881 patent/CN202935578U/en not_active Expired - Fee Related
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| CN203528804U (en) | Large-size rescue amphibious aircraft | |
| CN203528820U (en) | Large-scale fire extinguishing amphibious airplane | |
| CN106043689A (en) | Vertical take-off auxiliary system for top-mounted fixed-wing aircraft | |
| CN104276281A (en) | One-man flight vehicle | |
| CN205971845U (en) | Backpack fixed wing aircraft vertical take -off auxiliary system | |
| CN106864744B (en) | Coaxial rotor variant VTOL aircraft | |
| CN203434576U (en) | Remote-controlled multi-shaft unmanned plane paying-off device | |
| CN205273843U (en) | Many rotor unmanned aerial vehicle's multi -functional undercarriage | |
| CN204210731U (en) | Autogyro | |
| CN206141828U (en) | Unmanned rotation rotor helicopter | |
| CN202935581U (en) | Rotor wing protection framework device | |
| CN202935577U (en) | Rotor wing protection framework device | |
| CN205044954U (en) | Coaxial two thick liquid hybrid gyroplane | |
| CN102424105B (en) | Powered flight fire balloon | |
| CN202935578U (en) | Rotor wing protection framework device | |
| CN204264444U (en) | Joined wing configuration aircraft during high lift length boat | |
| CN203428026U (en) | Small duct-type aircraft | |
| CN205652335U (en) | Oil of big load ratio moves fixed -wing aircraft | |
| CN103523230A (en) | Landing assistant parachute of unmanned aerial vehicle | |
| CN202481307U (en) | Four-propeller aircraft taking off and landing vertically | |
| CN205524948U (en) | Unmanned autogyro | |
| CN109018376A (en) | A kind of fixed-wing electric power cruise unmanned plane | |
| CN204507264U (en) | A kind of safe manned craft | |
| CN211435086U (en) | Novel power model airplane | |
| CN202935576U (en) | Coaxial aircraft |
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 |