CN205418053U - Modular overall arrangement of variant aircraft - Google Patents
Modular overall arrangement of variant aircraft Download PDFInfo
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- CN205418053U CN205418053U CN201521031479.1U CN201521031479U CN205418053U CN 205418053 U CN205418053 U CN 205418053U CN 201521031479 U CN201521031479 U CN 201521031479U CN 205418053 U CN205418053 U CN 205418053U
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Abstract
The utility model relates to an all -wing aircraft formula aircraft layout structure that can intercombination, and combination - decomposition variant mode. This scheme adoption is overlooked the shape and is the rhombus, has the all -wing aircraft formula overall arrangement of double arc line symmetrical profile section, when providing the condition for the combination variant, has better lift -to -drag to compare, this scheme adopts the trailing edge to open up long fracture formula elevator entirely as the chain of command to driftage control mode is regarded as with the resistance difference of the differential fracture in both sides to closed deflection as every single move, lift -over control mode, when fracture formula elevator open completely, in another aircraft of the same kind can wedge it with the leading edge to mechanism's locking, fracture formula elevator cover the joining region top, and the pipe fairing that keeps the surface is with airtight, through the combination variant, list the aircraft that can make little aspect ratio, has a supersonic flight ability makes up and becomes the combination aircraft that has big aspect ratio to obtain higher subsonic speed lift -to -drag and compare, can carry out the efficient shipping of fuel.
Description
Technical field
This patent is aircraft layout designs, belongs to technical field of aircraft design.
Background technology
Morphing aircraft is change of flight device layout parameter under different flying conditions, thus change of flight device aeroperformance, it is allowed to aircraft distribution form optimized to current flight conditions.Typical its variant designs includes, variable-sweep wing, variable incidence wing, straight line or rotary extension wing, change dihedral or folded wing, rotating engine cabin, deflection head or tail etc., these its variant designs have been applied on the aircrafts such as F-14, F-8, XB-70, V-22, consonance.But existing variant way of realization exists, and variant drive mechanism is complicated, fault rate is high and is difficult to safeguard, variant interrupts original structure and connects, weakens structural-load-carrying capacity and make construction weight increase, variant produces discontinuous gap, surface, step, fold etc. increases the major defect that the impact such as resistance and Radar Cross Section uses, and is allowed to after the 1980's fade away on the aircraft of design.Research in recent years use intellectual material, the technical research such as micro electronmechanical intelligent morphing aircraft due to basic technology still in the exploratory stage, deflection and driving force are the most limited, it is only applicable to the microsize aircraft of research, it is difficult to play effectiveness on full-scale practical aircraft.
Combination aircraft is to be combined by two or more aircraft, extends its use field or the mode of flight performance, and typical combination aircraft is " Herba Visci " combination " snowstorm " space shuttle etc. with aircraft with rocket combination of the plug-in fighter plane of bomber.But tradition " microscope carrier-parasitism " compound mode heavy damage original flight vehicle aerodynamic profile, carry aircraft does not the most produce thrust, make microscope carrier flying quality degradation, generally combination aircraft only has the ability awing decomposed, i.e. by the aircraft of microscope carrier release carry, and can not reconfigure.
Summary of the invention
It is an object of the invention to:
This patent proposes the aerodynamic configuration of aircraft of a kind of combined variant and combinations thereof variant manner, realize awing by parameters such as combination change of flight device wing load, aspect ratios, realize the different aeroperformance feature such as low supersonic drag, high subsonic speed lift-drag ratio, and keep the stealth capabilities of aircraft and combination aircraft thrust-weight ratio not to change with combination or decomposition.
The technical scheme is that
The parts of this patent include:
A kind of combination type morphing aircraft layout structure, this layout includes the dead bolt within flying wing type fuselage, inner side cracking elevator, outside cracking elevator, knapsack power device, body trailing edge and the locking mechanism of body leading edge, sees accompanying drawing 1, accompanying drawing 2.
Flying wing type fuselage is symmetrical airfoil section, plan view shape is rhombus, flying wing type fuselage trailing edge is full length chain of command, chain of command form is divided into inner side cracking elevator and the outside cracking elevator of inside and outside 2 sections, being articulated with on fuselage, power set are born at aircraft back, and the collection of aircraft leading edge has locking mechanism, the inner side cracking elevator of aircraft trailing edge and outside cracking elevator expansible, its inwall has dead bolt；After inner side cracking elevator and outside cracking elevator open, the side leading edge of another aircraft can wedge inner space, pins the dead bolt of front aircraft trailing edge with the locking mechanism of leading edge, thus completes combination；By combination, the straight wing of class, swept-back wing or forward-swept-wing configuration form can be become by variant.The invention have the advantage that
(1) single aircraft itself is not required to be variant and pays additional cost, but the flight configuration required for can being obtained by combination when needed, thus obtain the aerodynamic advantages of variant.
(2) variant is not realized by special driver part, reduces mechanism complexity.
(3) latch mechanism needed for combinatory variants can be attached on the main load-carrying construction of aircraft, is conducive to obtaining high intensity, the Flight Vehicle Structure of weight amount.
(4) owing to using symmetrical airfoil section, aircraft can take upset combination, can avoid the interfering of aircraft power device jet flow before and after after combination to greatest extent, can be when larger amt combine, and holding thrust-weight ratio does not declines.
(5) cracking elevator is covered in junction, the fairing on binding site surface can be kept with airtight, it is to avoid have a negative impact surface flow field.
(6) push away resistance equilibrium condition according to assembly high lift-drag ratio aircraft, engine behavior can be reduced to save fuel oil.
(7) multiple different variant distribution form can be produced by the combination of varying number and arrangement mode.
Accompanying drawing explanation
Accompanying drawing 1 (a) is the top view of the layout of single aircraft；
Accompanying drawing 1 (b) is the side view of the layout of single aircraft；
Accompanying drawing 1 (c) is the front view of the layout of single aircraft；
Accompanying drawing 2 (a) is the front view of the primary clustering of single aircraft；
Accompanying drawing 2 (b) is the lateral side view of the primary clustering of single aircraft；
Accompanying drawing 3 combinatory variants way of realization；
Each component names:
Cracking elevator outside cracking elevator 3-inside 1-flying wing type fuselage 2-
The locking mechanism of the dead bolt 6-body leading edge within 4-knapsack power device 5-body trailing edge and other complementary structural bearings, hinge and installed part.
Detailed description of the invention
A kind of combination type morphing aircraft layout structure, this layout includes the dead bolt within flying wing type fuselage, inner side cracking elevator, outside cracking elevator, knapsack power device, body trailing edge and the locking mechanism of body leading edge, sees accompanying drawing 1, accompanying drawing 2.
Flying wing type fuselage is symmetrical airfoil section, and plan view shape is rhombus, has less wetted area, sufficient internal capacity and preferable transonic speed area distributions.
Flying wing type fuselage trailing edge is full length chain of command, chain of command form is divided into inner side cracking elevator and the outside cracking elevator of inside and outside 2 sections, it is articulated with on fuselage, power set are born at aircraft back, the collection of aircraft leading edge has locking mechanism, the inner side cracking elevator of aircraft trailing edge and outside cracking elevator expansible, its inwall has dead bolt；After inner side cracking elevator and outside cracking elevator open, the side leading edge of another aircraft can wedge inner space, pins the dead bolt of front aircraft trailing edge with the locking mechanism of leading edge, thus completes combination；By combination, the straight wing of class, swept-back wing or forward-swept-wing configuration form can be become by variant.
Cracking elevator has a following operating modes:
Guan Bi synchronizes deflection mode, lifting rudder action；
Close differential deflection, play aileron effect and control rolling；
Synchronization is opened, and plays flap effect；
Differential open, play drag direction rudder action；
Synchronization is opened, and inner space accommodates another aircraft leading edge, plays combinatory variants effect.
When needs carry out high-speed flight or need stealthy maneuverability ground conduct combat, fly with monomer flight state, when needs are implemented remote shipping with greater efficiency or are needed to hide the specific demands such as number of vehicles, by opening cracking elevator, agreed with by the locking mechanism of the dead bolt within body trailing edge with another aircraft body leading edge, locking combination can be realized, there is certain elastic cracking elevator and cover on binding site surface.
Claims (1)
1. a combination type morphing aircraft layout structure, is characterized in that, this layout structure includes the dead bolt within flying wing type fuselage, inner side cracking elevator, outside cracking elevator, knapsack power device, body trailing edge and the locking mechanism of body leading edge；
Flying wing type fuselage is symmetrical airfoil section, plan view shape is rhombus, flying wing type fuselage trailing edge is full length chain of command, chain of command form is divided into inner side cracking elevator and the outside cracking elevator of inside and outside 2 sections, being articulated with on fuselage, power set are born at aircraft back, and the collection of aircraft leading edge has locking mechanism, the inner side cracking elevator of aircraft trailing edge and outside cracking elevator expansible, its inwall has dead bolt；After inner side cracking elevator and outside cracking elevator open, the side leading edge of another aircraft can wedge inner space, pins the dead bolt of front aircraft trailing edge with the locking mechanism of leading edge, thus completes combination；By combination, the straight wing of class, swept-back wing or forward-swept-wing configuration form can be become by variant.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201521031479.1U CN205418053U (en) | 2015-12-11 | 2015-12-11 | Modular overall arrangement of variant aircraft |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201521031479.1U CN205418053U (en) | 2015-12-11 | 2015-12-11 | Modular overall arrangement of variant aircraft |
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| Publication Number | Publication Date |
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| CN205418053U true CN205418053U (en) | 2016-08-03 |
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| CN201521031479.1U Active CN205418053U (en) | 2015-12-11 | 2015-12-11 | Modular overall arrangement of variant aircraft |
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Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN107512382A (en) * | 2017-08-01 | 2017-12-26 | 中国航空工业集团公司西安飞机设计研究所 | One kind combination aircraft |
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2015
- 2015-12-11 CN CN201521031479.1U patent/CN205418053U/en active Active
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN107512382A (en) * | 2017-08-01 | 2017-12-26 | 中国航空工业集团公司西安飞机设计研究所 | One kind combination aircraft |
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