CN101891016A - Invisible autogyro - Google Patents
Invisible autogyro Download PDFInfo
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- CN101891016A CN101891016A CN2009101465081A CN200910146508A CN101891016A CN 101891016 A CN101891016 A CN 101891016A CN 2009101465081 A CN2009101465081 A CN 2009101465081A CN 200910146508 A CN200910146508 A CN 200910146508A CN 101891016 A CN101891016 A CN 101891016A
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Abstract
The invention discloses an invisible autogyro, which comprises a vertically arranged middle bracket, a front bracket, an empennage bracket and two lateral wheel brackets, wherein the top end of the middle bracket is pivoted with a rotary wing and is fixedly provided with a seat and an oil tank respectively; one end of the front bracket is connected with the bottom end of the middle bracket and extends forwards; one end of the empennage bracket is connected with the bottom end of the middle bracket and extends backwards; the lateral wheel brackets are arranged on two sides of the middle bracket respectively; and the middle bracket, the front bracket, the empennage bracket, the lateral wheel brackets, the seats, a propeller, the rotary wing and an empennage are all made of a high-strength fiber material, and a thermal-insulation layer is arranged around an engine. Through the design, the main parts of the autogyro are all made of the high-strength fiber material, so when flying in the air, the autogyro cannot be detected by radar; and the thermal-insulation layer is arranged around the engine for shielding the heat of the engine and avoiding infrared detection, so the invisible effect is improved greatly.
Description
Technical field
The present invention relates to a kind of aircraft, refer to a kind of stealthy self rotor aircraft especially.
Background technology
Former from cyclogyro is a kind of ancient type, comes out early than helicopter.But the back is because of the comfort feature of the invention of helicopter and vertical takeoff and landing, be in early days from cyclogyro can not, thereby be eliminated at that time from cyclogyro.
Near for some years because the generation of up-to-date technology makes this ancient machine be paid attention to by people again.It simple in structure mainly comprises a main framing, and main framing is provided with devices such as seat, engine, screw propeller and fuel tank, is generally positioned at the top of main framing from rotor; In addition, also need front-wheel and side wheel be set respectively in the front end and the both sides of main framing; Travel forward to promote aircraft by the rotation of driven by engine screw propeller during use, the angle of adjusting simultaneously from rotor of facining the wind makes aircraft takeoff to produce enough big buoyancy.
Because the flexible characteristic of this kind aircraft has obtained increasing application at present in military activity, substitute original helicopter from cyclogyro as what the shore patrol of the U.S. now just used 4 people's seats.But the major part of self rotor aircraft all is to use metallic material to make as main framing, seat, screw propeller etc. at present, is difficult to hide the detection of radar, because driving engine can produce a large amount of heats when work, also can be detected by infra-red detection in addition; In military activity, more and more higher to the disguise requirement of aircraft at present no matter be investigation or attack, therefore, need really present self rotor aircraft is done further improvement.
Summary of the invention
Therefore the technical problem to be solved in the present invention can be hidden radar detection and infra-red detection simultaneously for a kind of later-model self rotor aircraft is provided, and improves hidden function greatly.
For solving the problems of the technologies described above, the invention provides a kind of stealthy self rotor aircraft, comprise: a medium-height trestle that vertically is provided with, described medium-height trestle top is pivoted with one from rotor, described medium-height trestle front side is pressed close to medium-height trestle and is installed with a seat, described medium-height trestle rear side is pressed close to medium-height trestle and is provided with engine and fuel tank, and described engine power mouth is provided with a screw propeller; One front frame, an end of described front frame is connected in the bottom of described medium-height trestle, and extends forward, and described front frame is not provided with a front-wheel with medium-height trestle bonded assembly one end; One empennage support, an end of described empennage support is connected in the bottom of described medium-height trestle, and extends back, and described empennage support is not provided with an empennage with medium-height trestle bonded assembly one end; The both sides wheel support is arranged at the both sides of described medium-height trestle respectively; Described medium-height trestle, front frame, empennage support, side wheel support, seat, screw propeller, all adopt high tensile strength fibrous material to make, and be provided with one deck thermal insulation layer around the described engine from rotor and empennage.
By this design, the major part of this kind self rotor aircraft all adopts nonmetallic high tensile strength fibrous material to make, radar is undetectable when aloft flying, also around engine, be provided with one deck thermal insulation layer simultaneously, engine is carried out thermoshield to hide infra-red detection, improved hidden function greatly.
Further improvement of the present invention is that described high tensile strength fibrous material is carbon fiber or glass fibre.
Further improvement of the present invention is that an end of described front frame adopts pivotable mode to be connected in the bottom of described medium-height trestle; One end of described empennage support adopts pivotable mode to be connected in the bottom of described medium-height trestle; Described side wheel support comprises three connecting rods, vertically is followed successively by boxed rod, middle connecting rod and lower link, and an end of described boxed rod and middle connecting rod is hubbed on the medium-height trestle, and an end of described lower link is connected on the front frame removably; Described three connecting rods do not interconnect with the medium-height trestle and the front frame bonded assembly other end.By this design, self rotor aircraft can carry out folding when not using, greatly reduce storage space.
Description of drawings
Fig. 1 is the schematic perspective view of aircraft of the present invention;
Fig. 2 is the decomposing schematic representation of aircraft of the present invention;
Fig. 3 is the folding process scheme drawing of aircraft of the present invention;
Fig. 4 is the folding back scheme drawing of aircraft of the present invention.
The specific embodiment
The invention will be further described below in conjunction with the drawings and specific embodiments.
Consult Fig. 1 and shown in Figure 2, aircraft 10 of the present invention mainly comprises medium-height trestle 20, adopts can pivot bonded assembly front frame 30, empennage support 40, both sides wheel support 50 with medium-height trestle 20, wherein:
Described medium-height trestle 20 is a rod shaped structure that vertically is provided with, and its top is pivoted with one from rotor 21, should can assemble by some fins from rotor 21; The front side of medium-height trestle 20 is pressed close to medium-height trestle 20 and is installed with a back of seat 22, and medium-height trestle 20 rear sides are pressed close to medium-height trestle and are provided with engine 23; The bottom of described medium-height trestle 20 is provided with the tank hanger 24 of an arc, and putting on the shelf at this tank hanger 24 is provided with fuel tank 25, and fuel tank 25 is connected with engine 23 by transport pipe, and the clutch end of engine 23 is provided with a screw propeller 26; Back of seat 22 dead aheads are provided with joystick 27, this joystick 27 by linkage structure (can be mechanisms such as rope or connecting rod) be connected from rotor 21, the user can control the facing the wind angle of joystick 27 control from rotor 21;
Described front frame 30 1 ends are hubbed at the bottom of described medium-height trestle 20, and extend forward, and front frame 30 is not pivoted with a front-wheel support 31 with medium-height trestle 20 bonded assemblys one end, and front-wheel support 31 is put on the shelf and is provided with front-wheel 32; Front-wheel support 30 front ends are provided with pedal 33, and pedal 33 keeps interlock with front-wheel support 31, by the direct of travel of pushes pedals 33 may command front-wheels 32; Respective seat chair back 22 positions also are installed with seat support 34 on front frame 30;
Described empennage support 40 middle parts are recessed roughly to become one " V " shape, the one end is hubbed at the bottom of described medium-height trestle 20, and extend back, empennage support 40 is not provided with empennage 41 with medium-height trestle 20 bonded assemblys one end, and under empennage support 40 middle parts position of the just in time corresponding described fuel tank 25 of recess; Empennage comprises that a fixing horizontal tail 411 and is arranged at the vertical wing 412 on the described horizontal tail 411, and the described vertical wing 412 bottoms are provided with a vertical pivot 413, thereby described pedal 33 is connected the rotation of handling the described vertical wing 412 by rope with vertical pivot 413;
Both sides wheel support 50 is symmetricly set in the both sides of medium-height trestle 20 respectively, side wheel support 50 comprises three connecting rods, vertically be followed successively by boxed rod 51, middle connecting rod 52 and lower link 53, described boxed rod 5 is hubbed on the medium-height trestle 50 with an end of middle connecting rod 52, one end of lower link 53 is connected on the front frame 30 removably, and three connecting rods do not interconnect with the medium-height trestle 50 and the front frame 30 bonded assembly other ends and are provided with side wheel 54 at this end, the moulding thus of whole side wheel support 50;
Described medium-height trestle 20, front frame 30, empennage support 40, side wheel support 50, chair back 22, seat support 32, screw propeller 25, all adopt high tensile strength fibrous material to make from rotor 21 and empennage 41, hide the detection of radar in order to antagonism, as preferred embodiment of the present invention, this kind high tensile strength fibrous material can be selected carbon fiber or glass fibre for use; Be provided with one deck thermal insulation layer 231 around the simultaneously described engine 23, this layer thermal insulation layer can be made by asbestos cloth, asbestos board or other materials, utilize 231 pairs of engines of this heat insulation laminate 23 to carry out thermoshield and hide infra-red detection, further improved hidden function with antagonism.
Consult Fig. 3 and shown in Figure 4, self rotor aircraft 10 of the present invention is in transportation and storage, to pull down from parts such as rotor 21, front-wheel support 31, front-wheel 32, side wheel 54, empennage 41, back of seat 22, seat support 34 and joysticks 27 earlier, again by the annexation that is pivoted between front frame 30, empennage support 40, both sides wheel support 50 and the medium-height trestle 20, with front frame 30, empennage support 40, both sides wheel support 50 to medium-height trestle 20 direction foldings; Wherein, when folding side wheel support 50, need earlier an end of lower link 53 is disassembled from front frame 30, and then with boxed rod 51, the medium-height trestle 20 direction foldings in the same way of middle connecting rod 52 1; As shown in Figure 4, through after the folding, the front frame 30 of aircraft 10, empennage support 40 and both sides wheel support 50 medium-height trestle 20 of all fitting no longer occupies additional space and reduces greatly, only need a chest just can load and transport, for transportation and storage have brought bigger facility.
Claims (7)
1. stealthy self rotor aircraft comprises:
One medium-height trestle that vertically is provided with, described medium-height trestle top is pivoted with one from rotor, and described medium-height trestle front side is pressed close to medium-height trestle and is installed with a seat, and described medium-height trestle rear side is pressed close to medium-height trestle and is provided with engine and fuel tank, and described engine power mouth is provided with a screw propeller;
One front frame, an end of described front frame is connected in the bottom of described medium-height trestle, and extends forward, and described front frame is not provided with a front-wheel with medium-height trestle bonded assembly one end;
One empennage support, an end of described empennage support is connected in the bottom of described medium-height trestle, and extends back, and described empennage support is not provided with an empennage with medium-height trestle bonded assembly one end;
The both sides wheel support is arranged at the both sides of described medium-height trestle respectively;
It is characterized in that: described medium-height trestle, front frame, empennage support, side wheel support, seat, screw propeller, all adopt high tensile strength fibrous material to make, and be provided with one deck thermal insulation layer around the described engine from rotor and empennage.
2. aircraft as claimed in claim 1 is characterized in that, described high tensile strength fibrous material is a carbon fiber.
3. aircraft as claimed in claim 1 is characterized in that, described high tensile strength fibrous material is a glass fibre.
4. as claim 1,2 or 3 described aircraft, it is characterized in that an end of described front frame adopts pivotable mode to be connected in the bottom of described medium-height trestle; One end of described empennage support adopts pivotable mode to be connected in the bottom of described medium-height trestle; Described side wheel support comprises three connecting rods, vertically is followed successively by boxed rod, middle connecting rod and lower link, and an end of described boxed rod and middle connecting rod is hubbed on the medium-height trestle, and an end of described lower link is connected on the front frame removably; Described three connecting rods do not interconnect with the medium-height trestle and the front frame bonded assembly other end.
5. aircraft as claimed in claim 4, it is characterized in that, described empennage comprises that a fixing horizontal tail and is arranged at the vertical wing on the described horizontal tail, and described front frame is provided with pedal, thereby described pedal is connected the rotation of handling the described vertical wing by rope with vertical pivot.
6. aircraft as claimed in claim 4 is characterized in that, the support interlock of described pedal and described front-wheel.
7. aircraft as claimed in claim 4 is characterized in that, described seat the place ahead is provided with described joystick from rotor.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN2009101465081A CN101891016A (en) | 2009-05-19 | 2009-05-25 | Invisible autogyro |
Applications Claiming Priority (3)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN200920072548 | 2009-05-19 | ||
| CN200920072548.1 | 2009-05-19 | ||
| CN2009101465081A CN101891016A (en) | 2009-05-19 | 2009-05-25 | Invisible autogyro |
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| Publication Number | Publication Date |
|---|---|
| CN101891016A true CN101891016A (en) | 2010-11-24 |
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| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN2009101465081A Pending CN101891016A (en) | 2009-05-19 | 2009-05-25 | Invisible autogyro |
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Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN102328746A (en) * | 2011-07-05 | 2012-01-25 | 罗晓晖 | Bag-release delay-control-type invisible bombing system of aircraft |
| CN103569357A (en) * | 2012-07-31 | 2014-02-12 | 赵秋顺 | Large high-strength composite carbon fiber rotor wing |
| CN108791868A (en) * | 2018-07-31 | 2018-11-13 | 刘浩然 | A kind of new transport unmanned plane of safety and stability |
Citations (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN1136522A (en) * | 1995-05-22 | 1996-11-27 | 赵增光 | High safety rotary wing aviation craft |
| CN1876495A (en) * | 2006-06-28 | 2006-12-13 | 孙为红 | Coaxial double-oared self-spinning wing aircraft with fixed wing |
-
2009
- 2009-05-25 CN CN2009101465081A patent/CN101891016A/en active Pending
Patent Citations (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN1136522A (en) * | 1995-05-22 | 1996-11-27 | 赵增光 | High safety rotary wing aviation craft |
| CN1876495A (en) * | 2006-06-28 | 2006-12-13 | 孙为红 | Coaxial double-oared self-spinning wing aircraft with fixed wing |
Non-Patent Citations (1)
| Title |
|---|
| 刘晓山、郑立胜: "《飞机修理新技术》", 31 May 2006, 国防工业出版社 * |
Cited By (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN102328746A (en) * | 2011-07-05 | 2012-01-25 | 罗晓晖 | Bag-release delay-control-type invisible bombing system of aircraft |
| CN102328746B (en) * | 2011-07-05 | 2015-04-15 | 罗晓晖 | Bag-release delay-control-type invisible bombing system of aircraft |
| CN103569357A (en) * | 2012-07-31 | 2014-02-12 | 赵秋顺 | Large high-strength composite carbon fiber rotor wing |
| CN108791868A (en) * | 2018-07-31 | 2018-11-13 | 刘浩然 | A kind of new transport unmanned plane of safety and stability |
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Application publication date: 20101124 |