CN103809589A - Proof machine - Google Patents
Proof machine Download PDFInfo
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- CN103809589A CN103809589A CN201210446455.7A CN201210446455A CN103809589A CN 103809589 A CN103809589 A CN 103809589A CN 201210446455 A CN201210446455 A CN 201210446455A CN 103809589 A CN103809589 A CN 103809589A
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Abstract
The invention discloses a proof machine. The proof machine is composed of a wing (1), an undercarriage (2), a connection rack (3), a head (4), a tiltable intermediate section wing and main power system (5), a vertical empennage rotor wing (6), a vertical empennage (7), a tailplane (8), a rotor wing (9), a frame (10) and a wing rotor wing (11). The proof machine employs a unique tiltable intermediate section wing body/main power system and a variable pitch posture adjusting power system and is comprehensively applied to a single-tailboom aerodynamic layout so as to ensure that an airplane has quite good short-distance/vertical rising and landing performance and stable hovering performance, and is provided with excellent air cruise capability of a fixed wing airplane at the same time. The integrated tilt design of the intermediate section wing body and main power system can satisfy the need for tilting by a power system, and can also reduce the shield effects by the frame and the wing on propeller slip-stream during a tilting process.
Description
Technical field
The present invention relates to a kind of proof machine.
Background technology
Because tiltrotor aircraft has unique flight advantage, as far back as phase late 1940s, Bell Helicopter Company just starts its correlation technique to study.But there are the technological difficulties of a lot of self complexity in tiltrotor, the transition flight pattern of particularly verting dynamic instability, causes it to experience the development course of very long complications.China is also at the early-stage for the research of tiltrotor, there is no the design parameter of relevant tiltrotor aircraft, and many places are in theoretical research stage at present.
Based on the advantage that can free landing proof machine have merged helicopter and fixed wing aircraft of the power system of verting, it is a kind of dual-use high-tech product.This project will play good facilitation to the development of China's short distance, vertically taking off and landing flyer, short distance, vertically taking off and landing flyer that the proof machine forming develops into various ranks in the future have very wide application conversion prospect in many-side: monitor in the air in disaster area, battlefield aerial reconnaissance, in real time transmission of information; Air-borne early warning and coordinative command; Target indication, communication relaying, disaster area assessment, combat success assessment; Electronic interferences, attacks enemy's important goal; The inspection aerial platform in the fields such as agriculture forest and husbandry.This class aircraft more has its wide application prospect at sea, can meet the harsh requirement to airflight platform of warship and large vessel.Succeeding in developing of this project has significant economic and social benefit.
The present invention mainly for based on the power system of verting can be free landing checking utilize advantage and current demand, a kind of more advanced and applicable tiltrotor aircraft is provided.
Summary of the invention
The technical solution used in the present invention is: a kind of small-sized tiltrotor aircraft, comprising: the compositions such as rotor, wing, fuselage, tailplane, vertical tail, the stage casing wing body that can vert, main power system, displacement posture adjustment power system, head, link, undercarriage and flight control system; Whole aircraft adopts succinct grafting pattern, and complete machine is decomposed into six parts, has reduced the shared space of aircraft, is conducive to transportation; Posture adjustment control adopts unique afterbody motor posture adjustment pattern, has increased the arm of force, has strengthened control effect, also can provide part lift for aircraft simultaneously; Adopt novel electronics stability augmentation system, turn speed by series connection level meter control electricity, make the stability of hang obtain further reinforcement; Stage casing wing body verts to design and has adopted succinct inclining rotary mechanism for ease of maintenaince, utilizes receipts rope machine by primary speed-down, wing to be verted, and has reduced the cover impact of wing on engine downwash flow by tilting wing; Be installed on the posture adjustment power system of wing tip and afterbody, for moment and the sharp opposing external disturbance of balance main power system; Use digital gyro and laser gyro to increase steady technology, reduced the manipulation technology requirement to operator; This proof machine adopts three undercarriages, and adopts the fabulous Aseismatic Design of shock-absorbing capacity; Control system mainly comprises land station's supervisory system, airborne Flight Control Law, flight-control computer operating system, flight attitude signal processing unit.Hardware aspect comprises boat appearance measurement module (IMU), GPS receiver module, servo driving module, remote control decoding module and the flight control computer based on ARM framework; Described rotor has 5; Blade quantity is 3*5, and the wing rotor with it that wherein verts has rotor flying characteristic and the wind stick flying quality of helicopter concurrently.
The technique effect that the present invention realizes is: adopt unique verted stage casing wing body, main power system, displacement posture adjustment power system, and integrated application is in single shoe aerodynamic arrangement, to guarantee that aircraft has good short distance, vertical takeoff and landing performance and steadily hovering performance, there is the good aerial cruising ability of fixed wing aircraft simultaneously.The design of verting of the one of stage casing wing body and main power system, can meet the needs that power system is verted, and the bridging effect for propellerslip of process middle machine body and wing can reduce again to vert.This proof machine has helicopter flight pattern, vert offline mode and aircraft flight pattern.In the time of helicopter flight pattern, mainly provide force and moment by wing rotor and active force rotor; In the time of aircraft flight pattern, main power system rotor is total apart from handling the size that changes pulling force vector, is installed on the posture adjustment power system posture adjustment of wing tip and afterbody; In the time verting transition flight, mainly by controlling the corresponding relation of Yi Shen inclination angle, stage casing and flying speed, coordinate total square and longitudinal bending moment simultaneously, complete the transition mode flight of verting.
The technological merit that the present invention possesses and advantage: there is good advantage at aspects such as short distance, vertical takeoff and landing, hovering, no-radius turning, high maneuverability, long flying power, large load-carrying ability, strong interference rejection ability.
Accompanying drawing explanation
More specifically illustrate by the preferred embodiments of the present invention shown in accompanying drawing, above-mentioned and other object of the present invention, Characteristics and advantages will be more clear.In whole accompanying drawings, identical Reference numeral is indicated identical part.Deliberately do not draw accompanying drawing by physical size equal proportion convergent-divergent, focus on illustrating purport of the present invention.
Fig. 1 is the primary structure figure of proof machine transition flight
Fig. 2 is helicopter flight mode chart
Fig. 3 is fixed wing aircraft offline mode figure
Wherein, 1, wing 2, undercarriage 3, link 4, head 5, can vert stage casing wing and main power system 6, vertical tail rotor 7, vertical tail 8, tailplane 9, rotor 10, fuselage 11, wing rotor
Embodiment
Take off vertically with helicopter mode by ground monitoring system control proof machine, obtain certain forward flight speed in helicopter flight pattern, enter the ALT-CH alternate channel that verts, under aircraft mounted control system and external control hand operation compensation, realize transition mode flight, finally to fly before airplane-mode high speed; In the time landing, by verting of stage casing wing body, finally landed with helicopter mode by fly transition mode flight of airplane-mode; Proof machine can complete the instruction such as hovering, no-radius turning in the air according to being controlled at.Whole process can remote control control, or intelligent mode control.Can load according to actual needs different actuating equipments, such as the equipment of taking photo by plane and weapon etc.
Adopt novel electronics stability augmentation system, turn speed by series connection level meter control electricity, make the stability of hang obtain further reinforcement.Utilize receipts rope machine by primary speed-down, wing to be verted, reduced the cover impact of wing on engine downwash flow by tilting wing.Control system mainly comprises land station's supervisory system, airborne Flight Control Law, flight-control computer operating system, flight attitude signal processing unit; Hardware aspect comprises boat appearance measurement module (IMU), GPS receiver module, servo driving module, remote control decoding module and the flight control computer based on ARM framework.
Claims (10)
1. a proof machine, is made up of wing (1), undercarriage (2), link (3), head (4), can vert stage casing wing and main power system (5), vertical tail rotor (6), vertical tail (7), tailplane (8), rotor (9), fuselage (10), wing rotor (11).
2. proof machine according to claim 1, is characterized in that: its stage casing wing is as the wing body that can vert.
3. proof machine according to claim 1, is characterized in that: the design of verting that this stage casing wing body and main power system are integrated.
4. proof machine according to claim 1, is characterized in that: this power system adopts displacement posture adjustment power system, and is arranged on airplane wingtip and afterbody.
5. proof machine according to claim 1, is characterized in that: use digital gyro and laser gyro to increase steady technology.
6. proof machine according to claim 1, is characterized in that: whole aircraft adopts succinct grafting pattern, and complete machine is decomposed into six parts.
7. proof machine according to claim 1, is characterized in that: adopt three undercarriages, and adopt the fabulous Aseismatic Design of shock-absorbing capacity.
8. proof machine according to claim 1, is characterized in that: adopt novel electronics stability augmentation system, turn speed by series connection level meter control electricity, make the stability of hang obtain further reinforcement.
9. proof machine according to claim 1, is characterized in that: utilize receipts rope machine by primary speed-down, wing to be verted, reduced the cover impact of wing on engine downwash flow by tilting wing.
10. proof machine according to claim 1, is characterized in that: control system mainly comprises land station's supervisory system, airborne Flight Control Law, flight-control computer operating system, flight attitude signal processing unit; Hardware aspect comprises boat appearance measurement module (IMU), GPS receiver module, servo driving module, remote control decoding module and the flight control computer based on ARM framework.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201210446455.7A CN103809589A (en) | 2012-11-09 | 2012-11-09 | Proof machine |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201210446455.7A CN103809589A (en) | 2012-11-09 | 2012-11-09 | Proof machine |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN103809589A true CN103809589A (en) | 2014-05-21 |
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Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201210446455.7A Pending CN103809589A (en) | 2012-11-09 | 2012-11-09 | Proof machine |
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| Country | Link |
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| CN (1) | CN103809589A (en) |
Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN105173073A (en) * | 2015-10-08 | 2015-12-23 | 西北工业大学深圳研究院 | Composite lift force type unmanned aerial vehicle realizing vertical take-off and landing |
| CN105270622A (en) * | 2015-10-30 | 2016-01-27 | 佛山市神风航空科技有限公司 | Composite wing aircraft with dihedral angle |
| CN105539834A (en) * | 2016-01-12 | 2016-05-04 | 成都纵横自动化技术有限公司 | Composite-wing vertical take-off and landing unmanned aerial vehicle |
-
2012
- 2012-11-09 CN CN201210446455.7A patent/CN103809589A/en active Pending
Cited By (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN105173073A (en) * | 2015-10-08 | 2015-12-23 | 西北工业大学深圳研究院 | Composite lift force type unmanned aerial vehicle realizing vertical take-off and landing |
| CN105270622A (en) * | 2015-10-30 | 2016-01-27 | 佛山市神风航空科技有限公司 | Composite wing aircraft with dihedral angle |
| CN105270622B (en) * | 2015-10-30 | 2018-08-03 | 佛山市神风航空科技有限公司 | A kind of compound wing aircraft in the band upper counterangle |
| CN105539834A (en) * | 2016-01-12 | 2016-05-04 | 成都纵横自动化技术有限公司 | Composite-wing vertical take-off and landing unmanned aerial vehicle |
| CN105539834B (en) * | 2016-01-12 | 2018-08-21 | 成都纵横自动化技术有限公司 | A kind of composite wing vertical take-off and landing drone |
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Legal Events
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| C06 | Publication | ||
| PB01 | Publication | ||
| C02 | Deemed withdrawal of patent application after publication (patent law 2001) | ||
| WD01 | Invention patent application deemed withdrawn after publication |
Application publication date: 20140521 |