CN202063257U - Light multipurpose aircraft - Google Patents
Light multipurpose aircraft Download PDFInfo
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- CN202063257U CN202063257U CN2011200320196U CN201120032019U CN202063257U CN 202063257 U CN202063257 U CN 202063257U CN 2011200320196 U CN2011200320196 U CN 2011200320196U CN 201120032019 U CN201120032019 U CN 201120032019U CN 202063257 U CN202063257 U CN 202063257U
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Abstract
The utility model discloses a light multipurpose aircraft, which comprises an aircraft body, aircraft wings, a tail wing device, a landing gear, a main power device, an auxiliary power device, an aircraft unit protective system and an aviation control comprehensive body for controlling multipurpose aviation equipment. The aircraft unit protective system is away from an aircraft casing and an aircraft body load bearing components through arranging auxiliary and main devices into a form of multi-layer shielding according to an importance order. The biggest component density of the aircraft is subject to the most possible damage area and an angle of sight, in particular, the portion from the front to the lower portion and the portion from the lateral side to the aircraft head form an approximately 30-degree angle respectively with an approaching plane of a destroy device. The comprehensive body for controlling the multipurpose aviation equipment is provided with an aircraft unit alarming system which is used when exceeding a destroying angle of sight and connected with a voice information device of an electronic comprehensive body and the aviation control comprehensive body. The light multipurpose aircraft not only reduces weight of the aircraft and improves durability, but also provides the best protection for aircraft crews in the simplest form.
Description
Technical field
The utility model relates to aeronautical engineering, is specifically related to the aircraft on light multipurpose way.
Background technology
The defence and the attack performance of this aircraft are relatively good, but because fuselage is heavier, the sensitivity of aircraft and maneuvering performance all can not satisfy actual demand.
Publication number is that the Russ P of RU2252899 discloses a kind of maneuvering performance light-duty aircraft of high-mobility, multipurpose, wheeled vehicle preferably, this aircraft includes fuselage, wing, tail gear, take-off and landing device, engine installation and Comprehensive Control body, wherein, the Comprehensive Control body comprises Information Exchange System, be used to control the airborne digital computer system of flight and training and operation, exterior storage and information input system, Radio Inertial navigation and landing system, operating console is positioned at the integrated flight device control system of aviator and operator's passenger cabin, operating console is positioned at the weapon control system of aviator and operator's passenger cabin, electronic display, control and observation system ensemble, the emergency alarm plate, dual redundant air equipment control system, airborne target monitoring system, the voice messaging control system, electrical power system, inside and outside lighting installation, the emergency escape system ensemble, dual redundant power plant control system.In view of the above, Information Exchange System is divided into 3 independently multiline message interchange channels, between computing system and the air equipment control system, between electronic display, control and observation system ensemble and the comprehensive voyage control system system radially coupling is arranged.
Although the light-duty aircraft of above-described high-mobility, multipurpose, wheeled vehicle has had very big improvement on maneuvering performance and sensitivity,, this improvement is to be cost with the defence of sacrificing aircraft and attack performance.
" SU-25 attack plane and derivation machine thereof " (referring to Bedretdinov I.A., SU-25 attack plane and derivation machine M. thereof, 000 " B﹠amp; Co Publishing Group; the 15th page) literary composition discloses a kind of SU-25 attack plane; comprise fuselage; wing; tail gear; take-off and landing device; engine installation and Comprehensive Control body; wherein, the Comprehensive Control body comprises Information Exchange System; be used to control the airborne digital computer system of flight and training and operation; exterior storage and information input system; Radio Inertial navigation and landing system; operating console is positioned at the integrated flight device control system of aviator and operator's passenger cabin; operating console is positioned at the weapon control system of aviator and operator's passenger cabin; electronic display; control and observation system ensemble; the emergency alarm plate; electrical power system; lighting installation; the generator protection system; the emergency escape system ensemble; and power plant control system.Above-mentioned generator protection system form in it is: crew cabin (driving compartment) bottom is armoring fully, but fuel consumption bulkhead part is armoring, and engine nacelle covers on the dangerous direction of bullet, and also part is armoring.In addition, armoring cap and armoring vest also are the parts of aviator's equipment.
Although above-mentioned SU-25 attack plane and derivation machine thereof declare both to have alleviated aircraft weight, can guarantee all to surmount on maneuvering performance, sensitivity, defending performance and the attack performance heavy attack plane again, but, conscientiously study the structure of this product and its description of operation, find: the effect that this product can not reach in the specification sheets to be declared at all.
The utility model content
Technical problem to be solved in the utility model is to provide a kind of light multipurpose way aircraft, makes that its durability is promoted, the quality Dimension Characteristics reduces, and the realization versatility.
In order to solve the problems of the technologies described above, the technical solution of the utility model is like this:
A kind of light multipurpose way aircraft; comprise fuselage; wing; tail gear; take-off and landing device; the major impetus device; auxiliary power unit; the generator protection system; and the aviation control synthesis that is used to control the high-mobility, multipurpose, wheeled vehicle air equipment; described Comprehensive Control body by multiplexer channel respectively with one group of airborne electronic computer; left-hand engine electronic control system; record and checking system; navigation is connected with equipment of rising and falling and Comprehensive Control body; and by the code message circuit respectively with fuel adjusting and monitoring system; acoustic information equipment and composite electron display system connect; wherein
Described generator protection system be by will assisting and major equipment is arranged the form that forms multilayer screen according to sequence of importance, and away from casing and fuselage load-carrying unit;
The maximum component density of described aircraft depends on the most probable damage field and the angle of sight, is specially, forwardly-from the below and in the side-below head section, become about 30 to spend with the face that approaches that destroys device;
The described synthesis that is used to control the high-mobility, multipurpose, wheeled vehicle air equipment is furnished with the unit warning, and this unit warning is used when destroying the angle of sight exceeding, and described unit warning links to each other with the speech information equipment of electronics synthesis body and aviation control synthesis.
For head and the upper body of protecting the aviator better; improve the durability of aircraft; described generator protection system is equipped with quick detachable suspension armor plate; passive protection element and active protecting component be equipped with on this armor plate; the fuselage outside face most probable zone and the angle of sight under fire depended in the fixed position of described armor plate, and 1ift-drag ratio is depended in the manufacturing of described armor plate.
In the technique scheme, embedded quick detachable armor plate also can assemble in described generator protection system, and this armor plate is fixed in fuselage interior, perhaps is fixed in the device and equipment box surface and the bottom surface that are used for extra passive protection element.
The utility model has not only alleviated the weight of aircraft, has improved its durability, but also is that the crew provides best protection with the form of simplifying most.
Description of drawings
Fig. 1 is a lateral plan of the present utility model.
Fig. 2 is a front view of the present utility model.
Fig. 3 and Fig. 4 have shown that aircraft destroys the calculating of the device angle of sight.
Fig. 5 is the section-drawing of A-A among Fig. 1.
Fig. 6 is the section-drawing of B-B among Fig. 1.
Fig. 7 is the section-drawing of C-C among Fig. 1.
Fig. 8 is the section-drawing of D-D among Fig. 1.
Fig. 9 is the section-drawing of E-E among Fig. 1.
The constitution diagram that Figure 10 and Figure 11 are subjected to for driving compartment in the utility model.
The specific embodiment
Below in conjunction with drawings and Examples the utility model is further described.
As depicted in figs. 1 and 2, a kind of light multipurpose of the utility model way aircraft comprises fuselage 1, wing 2, tail gear 3, take-off and landing device 4, engine installation 5 and driving compartment 6, wherein,
Described driving compartment 6 is positioned at the aircraft head section, and its structure comprises seat 7 and base plate 8 as shown in Figure 5, and the below of described base plate 8 is provided with the preceding foot rest 9 of take-off and landing device, is positioned at the device 10 of aircraft head section, part fuselage 1 and aircraft coating 11;
In driving compartment 6 front portions unit warning 12 is installed, specifically referring to Fig. 7 and Fig. 8, this unit warning 12 is used when exceeding the destruction angle of sight, and described system 12 links to each other with the speech information equipment of electronics synthesis body and aviation control synthesis.
Shown in Fig. 3-11, attack aircraft if destroy device (bullets of 7.62 millimeters bores) from angle of sight A (forwardly-from the below) or angle of sight B (forwardly-from the side), equipment, part system, device 10, coating 11, base plate 8, driving compartment 6, fuselage 1 load-carrying unit will have adequate thickness obstruction bullet to pass, because specific apparatus, part system and device 10 only just can penetrate during near driving compartment 6 at bullet.In view of the above, equipment, part system and install 10 and should arrange according to sequence of importance, away from coating (casing) 11, fuselage 1 load-carrying unit (the maximum component density of equipment, and the part system should consider the most probable damage field and the angle of sight with the layout of device 10: become about 30 degree with the face that approaches that destroys device).Like this, angle of sight A and C form I type damage zone-do not need driving compartment 6 is implemented protection in these angles of sight.In addition, Fig. 3 has shown that the angle of sight is the part I type damage zone of B, described zone by take-off and landing device before foot rest 9 sealing, also need not protection.
Shown in Fig. 3-11, II type damage zone is positioned at from angle of sight B (from the below-forwardly) to angle of sight D () zone from the side-forwardly.In this zone, coating 11, driving compartment 6 base plates 8, equipment, part system and install 10, all not enough together with the gross thickness of aircraft load-carrying unit, can not cancel Additional Protection to crew module.For improving the reliability of generator protection in II type damage zone, the bottom surface and the surface that coating 11, suspension or Embedded quick detachable armor plate 13 should be fixed on fuselage interior and equipment, part system and install 10 shells.Described armor plate 13 and the material thickness that is used for the armor plate manufacturing are selected to answer reference device, part system and are installed 10 position and importance; specifically referring to Figure 10 and Figure 11; in addition; the manufacturing of hanging armor plate 13 also should be with reference to the expectation 1ift-drag ratio of corresponding hitch point; to reduce air resistance; simultaneously, hanging armor plate 13 should be equipped with passive and the active protecting component.
Shown in Fig. 4 and 8, angle of sight D forms III type damage zone, that is to say that aviator's head and upper body can not obtain reliable protection.In this case, protect the aviator by the armored glass and the discretionary protection device (armoring cap and armoring vest) of driving compartment 6.
The technical solution of the utility model, the form that can simplify most with counterweight and Flight Vehicle Design for aircraft is that the crew provides best protection.
Above-mentioned measure can improve the durability of aircraft, and the possibility that makes the aviator preserve from increases:
-the place ahead: (do not have armoring) to 0.76 from 0.424;
-side: (do not have armoring) to 0.6 from 0.2.
The utility model is selected near the most probable angle of sight of destroying device and the suitableeest destruction device of aircraft by the optimum utilization to safeguard procedures, can make the weight of additional generator protection device be relieved to 95Kg from 300Kg, also is about 1/3rd sizes.The technical solution of the utility model is by alleviating the possibility raising 40% that armoring counterweight protects the scheme of crew cabin the aviator can be preserved from.
Claims (3)
1. light multipurpose way aircraft; comprise fuselage; wing; tail gear; take-off and landing device; the major impetus device; auxiliary power unit; the generator protection system; and the aviation control synthesis that is used to control the high-mobility, multipurpose, wheeled vehicle air equipment; described Comprehensive Control body by multiplexer channel respectively with one group of airborne electronic computer; left-hand engine electronic control system; record and checking system; navigation is connected with equipment of rising and falling and Comprehensive Control body; and by the code message circuit respectively with fuel adjusting and monitoring system; acoustic information equipment and composite electron display system connect; it is characterized in that
Described generator protection system be by will assisting and major equipment is arranged the form that forms multilayer screen according to sequence of importance, and away from casing and fuselage load-carrying unit;
The described synthesis that is used to control the high-mobility, multipurpose, wheeled vehicle air equipment is furnished with the unit warning, and this unit warning is used when destroying the angle of sight exceeding, and described unit warning links to each other with the speech information equipment of electronics synthesis body and aviation control synthesis.
2. light multipurpose according to claim 1 way aircraft; it is characterized in that; described generator protection system is equipped with quick detachable suspension armor plate; passive protection element and active protecting component be equipped with on this armor plate; the fuselage outside face most probable zone and the angle of sight under fire depended in the fixed position of described armor plate, and 1ift-drag ratio is depended in the manufacturing of described armor plate.
3. light multipurpose according to claim 1 way aircraft; it is characterized in that; described generator protection system is equipped with embedded quick detachable armor plate, and this armor plate is fixed in fuselage interior, perhaps is fixed in the device and equipment box surface and the bottom surface that are used for extra passive protection element.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN2011200320196U CN202063257U (en) | 2011-01-25 | 2011-01-25 | Light multipurpose aircraft |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN2011200320196U CN202063257U (en) | 2011-01-25 | 2011-01-25 | Light multipurpose aircraft |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN202063257U true CN202063257U (en) | 2011-12-07 |
Family
ID=45057130
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN2011200320196U Expired - Fee Related CN202063257U (en) | 2011-01-25 | 2011-01-25 | Light multipurpose aircraft |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN202063257U (en) |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN104303016A (en) * | 2011-12-30 | 2015-01-21 | 航空集团联合控股公司 | Integrated complex of on-board equipment for multifunctional aeroplane |
-
2011
- 2011-01-25 CN CN2011200320196U patent/CN202063257U/en not_active Expired - Fee Related
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN104303016A (en) * | 2011-12-30 | 2015-01-21 | 航空集团联合控股公司 | Integrated complex of on-board equipment for multifunctional aeroplane |
| CN104303016B (en) * | 2011-12-30 | 2017-05-24 | 航空集团联合控股公司 | Integrated complex of on-board equipment for multifunctional aeroplane |
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Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| C14 | Grant of patent or utility model | ||
| GR01 | Patent grant | ||
| CF01 | Termination of patent right due to non-payment of annual fee |
Granted publication date: 20111207 Termination date: 20170125 |
|
| CF01 | Termination of patent right due to non-payment of annual fee |