CN202935573U - Aircraft flap device - Google Patents
Aircraft flap device Download PDFInfo
- Publication number
- CN202935573U CN202935573U CN 201220509550 CN201220509550U CN202935573U CN 202935573 U CN202935573 U CN 202935573U CN 201220509550 CN201220509550 CN 201220509550 CN 201220509550 U CN201220509550 U CN 201220509550U CN 202935573 U CN202935573 U CN 202935573U
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- Prior art keywords
- transmission shaft
- aircraft
- rotor
- cabin
- lower rotor
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Abstract
The utility model discloses an aircraft flap device which comprises flaps, an upper rotor wing, a lower rotor wing, a cabin, an engine compartment and a landing gear; base frames are symmetrically arranged on two sides of the upper part of the cabin; flap transmission shafts are arranged on the base frames; the flaps are arranged on the outer sides of the flap transmission shafts; driving arms are arranged on the flap transmission shafts; and hydraulic control devices are arranged between the base frames and the driving arm. The aircraft flap device has the advantages that the flaps are arranged to drive a coaxial aircraft to move forwards or backwards and turn left and right; the engine compartment is one of the heaviest components of the aircraft and is arranged under the cabin, so that though the length of a transmission shaft between the rotor wings and the engine compartment is increased, the vertical stability of the coaxial aircraft can be better; and the aircraft flap device has the advantages of simple structure and better safety performance.
Description
Technical field
The utility model relates to a kind of rotor craft, especially relates to a kind of aircraft flaps device.
Background technology
Existing rotor craft does not arrange wing flap, because the piggyback pod of existing rotor craft is arranged on the top in cabin, the center of gravity of aircraft is all in the upper end of aircraft like this, somewhat top-heavy, although its manoevreability is good, but its complex structure has so just improved technical requirements and material requirement that it is made, 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 is to provide a kind of simple in structure, coaxial aircraft that vertical stability is good.
The utility model solves the problems of the technologies described above the technical scheme that adopts; A kind of aircraft flaps device, comprise wing flap, upper rotor, lower rotor, cabin, piggyback pod and alighting gear, the bilateral symmetry that it is characterized in that top, described cabin is provided with pedestal, is provided with the wing flap transmission shaft on described pedestal, and the arranged outside of described wing flap transmission shaft has wing flap.
Be provided with actuating arm on described wing flap transmission shaft, be provided with hydraulic control device between described pedestal and described actuating arm.
Described upper rotor below is provided with lower rotor, described lower rotor below is provided with the cabin, below, described cabin is provided 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.
Be provided with the rotor transmission shaft between described variable-speed conversion device and described upper rotor, be provided with lower rotor transmission shaft between described variable-speed conversion device and described lower rotor, described lower rotor transmission shaft is arranged on the outside of described upper rotor transmission shaft, the arranged outside of described lower rotor transmission shaft has the oversheath pipe, and described protecting pipe is arranged on center, described cabin.
Described alighting gear comprises foot rest and connects matrix, described connection matrix is arranged on the lower end of aircraft underframe, be movably set with a plurality of foot rests on described connection matrix, be connected with the Telescopic buffer device on described foot rest, the upper shaft of described Telescopic buffer device is connected on the aircraft outside frame, and described a plurality of foot rests lower ends respectively is movably set with cardan wheel.
Be provided with down the Eight characters between described upper rotor and described upper rotor transmission shaft and add the prime time, be provided with the Eight characters between described lower rotor and described lower rotor transmission shaft and add the prime time.
The upper end of described upper rotor transmission shaft is provided with discharging rod.
Compared with prior art, the utility model bilateral symmetry above the cabin is provided with wing flap, the arranging of wing flap can drive advancing, retreating of coaxial aircraft and left/right rotation to.
Piggyback pod is one of aircraft maximum weight, and it is arranged under the cabin, although increased propeller shaft length between rotor and piggyback pod, can make like this vertical stability of coaxial aircraft better, and it is simple in structure, and safety performance is good.
Description of drawings
Fig. 1 is constructional drawing of the present utility model;
Fig. 2 is the broken view of piggyback pod of the present utility model;
Fig. 3 is transmission shaft component figure of the present utility model;
Fig. 4 is wing flap side-looking constructional drawing of the present utility model;
Fig. 5 is wing flap forward sight constructional drawing of the present utility model;
Fig. 6 is landing gear structure figure of the present utility model;
Landing gear structure figure when Fig. 7 is the utility model flight.
The specific embodiment
Embodiment is described in further detail the utility model below in conjunction with accompanying drawing.
A kind of aircraft flaps device, comprise wing flap 2, upper rotor 11, lower rotor 12, cabin 3, piggyback pod 4 and alighting gear, the bilateral symmetry of 3 tops, cabin is provided with pedestal 24, is provided with wing flap transmission shaft 21 on pedestal 24, and the arranged outside of wing flap transmission shaft 21 has wing flap 2.
Be provided with actuating arm 22 on wing flap transmission shaft 21, be provided with hydraulic control device 23 between pedestal 24 and actuating arm 22.
Be provided with rotor transmission shaft 61 between variable-speed conversion device 42 and upper rotor 11, be provided with lower rotor transmission shaft 62 between variable-speed conversion device 42 and lower rotor 12, lower rotor transmission shaft 62 is arranged on the outside of rotor transmission shaft 61, the arranged outside of lower rotor transmission shaft 62 has oversheath pipe 63, and protecting pipe 63 is arranged on the center in cabin 3.
Alighting gear comprises foot rest 52 and connects matrix 54, connect the lower end that matrix 54 is arranged on aircraft underframe 46, connect on matrix 54 and be movably set with a plurality of foot rests 52, be connected with Telescopic buffer device 51 on foot rest 52, the upper shaft of Telescopic buffer device 51 is connected on aircraft outside frame 45, and a plurality of foot rests 52 lower ends respectively are movably set with cardan wheel 53.
Be provided with down the Eight characters between upper rotor 11 and upper rotor transmission shaft 61 and add the prime time 13, be provided with the Eight characters between lower rotor 12 and lower rotor transmission shaft 62 and add the prime time 14.
The upper end of upper rotor transmission shaft 61 is provided with discharging rod 7.
Claims (7)
1. aircraft flaps device, comprise wing flap, upper rotor, lower rotor, cabin, piggyback pod and alighting gear, the bilateral symmetry that it is characterized in that top, described cabin is provided with pedestal, is provided with the wing flap transmission shaft on described pedestal, and the arranged outside of described wing flap transmission shaft has wing flap.
2. a kind of aircraft flaps device according to claim 1, is characterized in that being provided with actuating arm on described wing flap transmission shaft, is provided with hydraulic control device between described pedestal and described actuating arm.
3. a kind of aircraft flaps device according to claim 1, it is characterized in that being provided with lower rotor below described upper rotor, described lower rotor below is provided with the cabin, below, described cabin is provided 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.
4. a kind of aircraft flaps device according to claim 3, it is characterized in that being provided with the rotor transmission shaft between described variable-speed conversion device and described upper rotor, be provided with lower rotor transmission shaft between described variable-speed conversion device and described lower rotor, described lower rotor transmission shaft is arranged on the outside of described upper rotor transmission shaft, the arranged outside of described lower rotor transmission shaft has the oversheath pipe, and described protecting pipe is arranged on center, described cabin.
5. a kind of aircraft flaps device according to claim 1, it is characterized in that described alighting gear comprises foot rest and connects matrix, described connection matrix is arranged on the lower end of aircraft underframe, be movably set with a plurality of foot rests on described connection matrix, be connected with the Telescopic buffer device on described foot rest, the upper shaft of described Telescopic buffer device is connected on the aircraft outside frame, and described a plurality of foot rests lower ends respectively is movably set with cardan wheel.
6. a kind of aircraft flaps device according to claim 4, is characterized in that being provided with down the Eight characters between described upper rotor and described upper rotor transmission shaft adds the prime time, is provided with the Eight characters between described lower rotor and described lower rotor transmission shaft and adds the prime time.
7. a kind of aircraft flaps device according to claim 4, is characterized in that the upper end of described upper rotor transmission shaft is provided with discharging rod.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN 201220509550 CN202935573U (en) | 2012-10-08 | 2012-10-08 | Aircraft flap device |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN 201220509550 CN202935573U (en) | 2012-10-08 | 2012-10-08 | Aircraft flap device |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN202935573U true CN202935573U (en) | 2013-05-15 |
Family
ID=48319827
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN 201220509550 Expired - Fee Related CN202935573U (en) | 2012-10-08 | 2012-10-08 | Aircraft flap device |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN202935573U (en) |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN110104175A (en) * | 2019-04-24 | 2019-08-09 | 北京航空航天大学 | A kind of coaxial reversed pair is flutterred rotor mechanism |
-
2012
- 2012-10-08 CN CN 201220509550 patent/CN202935573U/en not_active Expired - Fee Related
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN110104175A (en) * | 2019-04-24 | 2019-08-09 | 北京航空航天大学 | A kind of coaxial reversed pair is flutterred rotor mechanism |
| CN110104175B (en) * | 2019-04-24 | 2021-03-09 | 北京航空航天大学 | Coaxial reverse double-flapping rotor wing mechanism |
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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: 20131008 |