CN208715479U - Modularization supersonic speed unmanned plane - Google Patents
Modularization supersonic speed unmanned plane Download PDFInfo
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- CN208715479U CN208715479U CN201821238245.8U CN201821238245U CN208715479U CN 208715479 U CN208715479 U CN 208715479U CN 201821238245 U CN201821238245 U CN 201821238245U CN 208715479 U CN208715479 U CN 208715479U
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Abstract
The utility model provides a kind of modularization supersonic speed unmanned plane, comprising: buffering energy-absorbing nose cone, mission payload cabin, center fuselage cabin, enging cabin and wing；The front end in mission payload cabin is connect with the rear removable of buffering energy-absorbing nose cone, the front end in center fuselage cabin is connect with the rear removable in mission payload cabin, and it is electrically connected with mission payload cabin, the front end of enging cabin is connect with the rear removable in center fuselage cabin, and electrically and piping connection with center fuselage cabin, the connecting end surface of wing and the side in center fuselage cabin are detachably connected, and are electrically connected with center fuselage cabin.Modularization supersonic speed unmanned plane provided by the utility model is made of multiple modules, and monomer size is smaller after disassembly, is transported and is dismounted convenient for transition.
Description
Technical field
The utility model relates to aviation aircraft technical field more particularly to a kind of modularization supersonic speed unmanned planes.
Background technique
Supersonic speed unmanned plane and subsonic aircraft general difference on aerodynamic configuration are larger, as supersonic speed unmanned aerial vehicle body is long
It is thin it is bigger, wing setting is larger, wing aspect ratio is smaller etc., this is because in supersonic flight, the shock wave of unmanned plane
Resistance is the chief component of full machine resistance, and full machine resistance is much larger than the resistance of subsonic flight, thus supersonic speed at this time
The primary goal of unmanned plane aerodynamic configuration design is exactly to reduce drag due to shock wave.One of the effective way for reducing drag due to shock wave is exactly to subtract
The maximum secting area of the small equivalent body of revolution of full machine, thus biggish slenderness ratio is presented in the body of supersonic speed unmanned plane, generally 12
More than；Another drag reduction approach is exactly to increase the angle of sweep of aerofoil, after shock wave cone when aerofoil being made to be in supersonic flight, from
And it is in wing in subcritical flow, therefore the wing setting of supersonic speed unmanned plane is larger；Due to flying for supersonic speed unmanned plane
Row span is larger, meets shape from low speed to ultrasonic pneumatic demand, and lift coefficient slope cannot be too big, and should use up
Amount increases stall angle, this is exactly the Aerodynamic Characteristics of low aspect ratio wing, therefore the aspect ratio of supersonic speed unmanned plane is typically small.
Unmanned aerial vehicle design is all based on what a kind of advantageous flying speed was designed at present, that is, based on cruising speed into
What row endurance and voyage designed, but requirement of the different aerial missions to flying speed and endurance is different, and some flights are appointed
Business needs higher speed, such as supersonic speed target drone for target, and some longer endurances of needs, such as reconnaissance and surveillance, while because
The limitation of carry ability, military unmanned air vehicle needs to change different mission payloads under the requirement of different combat duties at present, because of nobody
Machine avionics system integrated level is higher, and general replacement load need to be completed in internal field storehouse, needs to survey total system after the completion of replacement
Examination and inspection
However, in the process of implementing the utility model, present inventor's discovery, a type unmanned plane is difficult to meet a variety of
Mission requirements, general solution are the unmanned planes for different task design various configurations, but very strong for timeliness
Emergent battle task, this layout strategy is obviously unable to meet demand；Simultaneously as ground crew is in replacement load every time
It all needs to dismount load hatchcover, inevitably there is maloperation in operating process or damages the risk of other systems equipment.
Utility model content
(1) technical problems to be solved
Based on above-mentioned technical problem, the utility model provides a kind of modularization supersonic speed unmanned plane, to alleviate the prior art
In a kind of type of unmanned plane be difficult to meet multiple-task demand, while it is easy to operate by mistake during disassembling operations or damage other
The technical issues of system equipment.
(2) technical solution
The utility model provides a kind of modularization supersonic speed unmanned plane, comprising: buffering energy-absorbing nose cone, in unmanned aircraft parachute descent
Contact to earth energy-absorbing when landing, protects housing construction and airborne equipment；Mission payload cabin, the tail of front end and the buffering energy-absorbing nose cone
Portion is detachably connected, interior to install mission payload；The rear removable in center fuselage cabin, front end and the mission payload cabin connects
It connects, and is electrically connected with the mission payload cabin, it is interior that airborne Aerial Electronic Equipment, recorery parachute and fuel tank are installed；Enging cabin, before
End connect with the rear removable in the center fuselage cabin, and electrically and piping connection with the center fuselage cabin, interior to install
Turbojet, jet pipe and empennage；And wing, connecting end surface and the side in the center fuselage cabin detachably connect
It connects, and is electrically connected with the center fuselage cabin.
In some embodiments of the utility model, between the buffering energy-absorbing nose cone and the mission payload cabin, described
Matched between mission payload cabin and the center fuselage cabin and between the center fuselage cabin and the enging cabin using flange
It closes, and is detachably connected by radial bolts；Wherein, it is arranged on the enging cabin and the connecting end surface in the center fuselage cabin
There is shape for hat beam.
In some embodiments of the utility model, in which: the center fuselage cabin includes: auricle before inside, is set to
The side in the center fuselage cabin；Auricle behind inside is set to the side in the center fuselage cabin, with auricle before the inside
Axially spaced-apart along the center fuselage cabin is arranged；The wing include: outside before auricle, be set to the wing and it is described in
The connecting end surface of fuselage compartment is entreated, and is detachably connected with auricle before the inside；Auricle behind outside is set to the wing and institute
Before the connecting end surface for stating center fuselage cabin, with the outside auricle along the wing tangential interval be arranged, and with it is described interior
Auricle is detachably connected behind side.
In some embodiments of the utility model, in which: auricle includes: behind auricle and the inside before the inside
The first auricle and the second auricle being axially arranged along the center fuselage cabin；First auricle of auricle and institute before the inside
The second auricle is stated to be folded in front of the outside on the two sides of auricle；First auricle of auricle and described behind the inside
Two auricles are folded in behind the outside on the two sides of auricle.
In some embodiments of the utility model, ear behind auricle, the inside before auricle, the outside before the inside
The first through hole arranged along the vertical direction and the second through-hole are provided on auricle after piece and the outside；Wherein: in described
The diameter of the first through hole of auricle is 12mm before auricle and the outside before side；Before the inside before auricle and the outside
The diameter of second through-hole of auricle is 10mm；The first through hole of auricle behind auricle and the outside behind the inside
Diameter is 8mm；The diameter of second through-hole of auricle is 6mm behind auricle and the outside behind the inside.
In some embodiments of the utility model, the junction in the wing and the center fuselage cabin is provided with wing body
Rectify outer cover.
In some embodiments of the utility model, in which:
Be additionally provided in the wing: front-axle beam runs through beam to be I-shaped, through the entire wing；The back rest is C
Font short beam is connect with the front-axle beam, and is arranged with the front-axle beam in y font；Wherein, auricle and the front-axle beam before the outside
It connects, auricle is connect with the back rest behind the outside；The center fuselage cabin further include: two ring frames, the ring frame ring
Axis around the center fuselage cabin is arranged, and is arranged along the axially spaced-apart in the center fuselage cabin；Wherein, the inside vestibule
Auricle is connect with two ring frames respectively after piece and the inside；The wing further include: aileron rudder face, with the machine
The wing is connected by the both ends shaft of the aileron rudder face；The enging cabin further include: slab tail rudder face starts with described
Cabin is connected by wing root shaft；Wherein, the slab tail rudder face and aileron rudder face are complete sandwich multiple material structure, utilize four pieces
The three axes control of unmanned plane is realized in the deflection of rudder face.
In some embodiments of the utility model, the wing includes: supersonic wing, and angle of sweep is greater than 45 °, exhibition
String ratio is less than 4；And long endurance wing, angle of sweep are not less than 4 no more than 45 °, aspect ratio.
In some embodiments of the utility model, the mission payload cabin includes: the first task for loading corner reflector
Cabin；Load the second mission module of high definition aerial camera；And load the third mission module of photoelectric nacelle.
In some embodiments of the utility model, in which: the connection in the center fuselage cabin and the mission payload cabin
The connection of end face, the connecting end surface of the enging cabin and the center fuselage cabin and the wing and the center fuselage cabin
End face is provided with aerospace connectors；It is quick that the enging cabin and the connecting end surface in the center fuselage cabin are additionally provided with oil pipe
Connection valve.
(3) beneficial effect
It can be seen from the above technical proposal that modularization supersonic speed unmanned plane provided by the utility model is with beneficial below
One of effect or in which a part:
(1) modularization supersonic speed unmanned plane provided by the utility model is made of multiple modules, after disassembly monomer size compared with
It is small, it transports and dismounts convenient for transition；
(2) modularization supersonic speed unmanned plane provided by the utility model can quickly repair nobody by replacing failure bay section
Machine comes into operation rapidly, and average time for repair of breakdowns greatly shortens, and flexibly, two sets of unmanned planes can be realized for Flight Line Maintenance maintenance
Redundancy backup and multipurpose flight, the unmanned plane that comprehensive coverage equipment compares many types of single task role with system use cost will be more
It is low；
(3) modularization supersonic speed unmanned plane provided by the utility model can temporary emergency replacement mission payload and wing, fastly
Speed switching aerial mission, task compatibility are strong.
Detailed description of the invention
Fig. 1 is the structural blast schematic diagram of modularization supersonic speed unmanned plane provided by the embodiment of the utility model.
Fig. 2 is that buffering energy-absorbing nose cone and the flange in mission payload cabin cooperate company in modularization supersonic speed unmanned plane shown in Fig. 1
Connect schematic diagram.
Fig. 3 is the structural representation of wing and the connecting end surface in center fuselage cabin in modularization supersonic speed unmanned plane shown in Fig. 1
Figure.
Fig. 4 is the whole dress of modularization supersonic speed unmanned plane provided by the embodiment of the utility model (long endurance reconnaissance version)
With schematic diagram.
[the utility model embodiment main element symbol description in attached drawing]
10- buffering energy-absorbing nose cone；
20- mission payload cabin；
30- center fuselage cabin；
Auricle before on the inside of 31-；
Auricle after on the inside of 32-；
33- wing body rectifies outer cover；
34- shape for hat beam；
35- ring frame；
40- enging cabin；
41- slab tail rudder face；
50- wing；
Auricle before on the outside of 51-；
Auricle after on the outside of 52-；
53- front-axle beam；
The 54- back rest；
55- aileron rudder face；
60- radial bolts；
70- nut.
Specific embodiment
Modularization supersonic speed unmanned plane provided by the embodiment of the utility model can quickly repair nothing by replacing failure bay section
It is man-machine, it comes into operation rapidly, average time for repair of breakdowns greatly shortens, and flexibly, two sets of unmanned planes can be real for Flight Line Maintenance maintenance
Existing redundancy backup and multipurpose flight, the unmanned plane that comprehensive coverage equipment compares many types of single task role with system use cost will be more
It is low.
For the purpose of this utility model, technical solution and advantage is more clearly understood, below in conjunction with specific embodiment, and
Referring to attached drawing, the utility model is further described.
The utility model embodiment provides a kind of modularization supersonic speed unmanned plane, as shown in Figure 1, comprising: buffering energy-absorbing head
Cone 10, contact to earth energy-absorbing when unmanned aircraft parachute descent lands, and protects housing construction and airborne equipment；Mission payload cabin 20, front end
It is connect with the rear removable of buffering energy-absorbing nose cone 10, it is interior that mission payload is installed；Center fuselage cabin 30, front end and task carry
The rear removable in lotus cabin 20 connects, and is electrically connected with mission payload cabin 20, in the airborne Aerial Electronic Equipment of installation, recorery parachute and
Fuel tank, airborne Aerial Electronic Equipment are the equipment that must be loaded with of flying every time, including flight control computer, small-sized inertial navigation combination, electricity
Source converter, distributor, data-link transmitting-receiving combination, satellite antenna, data-link antenna etc., after recorery parachute is used for aerial mission
It lands and recycles, fuel tank is engine fuel storage tank, provides fuel for engine；Enging cabin 40, front end and center fuselage cabin
30 rear removable connection, and electrically sprayed with piping connection, interior installation turbojet, tail with center fuselage cabin 30
Pipe and empennage, engine are installed on the front frame end face of the bay section, and empennage and its executing agency are mounted on the top rectification of the bay section
In bulge；And wing 50, connecting end surface and the side in center fuselage cabin 30 are detachably connected, and with center fuselage cabin 30
Electrical connection, modularization supersonic speed unmanned plane provided by the embodiment of the utility model are made of multiple modules, monomer ruler after disassembly
It is very little smaller, it transports and dismounts convenient for transition, and can quickly repair unmanned plane by replacing failure bay section, come into operation rapidly,
Average time for repair of breakdowns greatly shortens, and flexibly, two sets of unmanned planes can realize redundancy backup and multipurpose for Flight Line Maintenance maintenance
Flight, comprehensive coverage equipment are lower with the system use cost unmanned plane for comparing many types of single task role.
In some embodiments of the utility model, as shown in Fig. 2, buffering energy-absorbing nose cone 10 and mission payload cabin 20 it
Between, matched between mission payload cabin 20 and center fuselage cabin 30 and between center fuselage cabin 30 and enging cabin 40 using flange
It closes, and is detachably connected by radial bolts 60 (and nut 70)；Wherein, the main biography of enging cabin 40 and center fuselage cabin 30
Power direction is that fuselage is axial, therefore shape for hat beam is provided on the connecting end surface in enging cabin 40 and center fuselage cabin 30, is used for
Transmission force load.
In some embodiments of the utility model, as shown in figure 3, center fuselage cabin 30 includes: auricle 31 before inside, if
It is placed in the side in center fuselage cabin 30；Auricle 32 behind inside are set to the side in center fuselage cabin 30, with auricle 31 before inside
Axially spaced-apart along center fuselage cabin is arranged.
In some embodiments of the utility model, as shown in figure 3, wing 50 includes: auricle 51 before outside, it is set to machine
The connecting end surface of the wing 50 and center fuselage cabin 30, and be detachably connected with auricle 31 before inside；And auricle 52 behind outside, if
It is placed in the connecting end surface of wing 50 Yu center fuselage cabin 30, is arranged with auricle 51 before outside along the tangential interval of wing 50, and
It is detachably connected with auricle 32 behind inside.
In some embodiments of the utility model, as shown in Figure 3, in which: auricle 32 behind auricle 31 and inside before inside
It include: the first auricle and the second auricle being axially arranged along center fuselage cabin 30；First auricle of auricle 31 and before inside
Two auricles be folded in outside before auricle 51 two sides on；The first auricle of auricle 32 and the second auricle are folded in outside behind inside
Afterwards on the two sides of auricle 52.
In some embodiments of the utility model, before inside before auricle 31, outside behind auricle 51, inside auricle 32 and
The first through hole arranged along the vertical direction and the second through-hole are provided with behind outside on auricle 52.
In some embodiments of the utility model, as shown in figure 3, before inside before auricle 31 and outside auricle 51 first
The diameter of through-hole is 12mm；The diameter of the second through-hole of auricle 51 is 10mm before auricle 31 and outside before inside；Auricle behind inside
32 and outside after auricle 52 first through hole diameter be 8mm；Second through-hole of auricle 52 behind auricle 32 and outside behind inside
Diameter is 6mm.
In some embodiments of the utility model, the junction in wing 50 and center fuselage cabin 30 is provided with the rectification of wing body
Outer cover 33.
In some embodiments of the utility model, as shown in figure 3, being additionally provided in wing 50: front-axle beam 53 is I-shaped
Shape runs through beam, runs through entire wing 50；And the back rest 54, it is C font short beam, is connect with front-axle beam 53, and is in y word with front-axle beam 53
Shape setting；Wherein, auricle 51 is connect with front-axle beam 53 before outside, and auricle 52 is connect with the back rest 54 behind outside.
In some embodiments of the utility model, center fuselage cabin 30 further include: two ring frames 35, the ring frame
35 axis around center fuselage cabin 30 is arranged, and is arranged along the axially spaced-apart in center fuselage cabin 30；Wherein, auricle 31 before inside
It is connect respectively with two ring frames 35 with auricle 32 behind inside, transmits shearing, moment of flexure and the torque of wing 50.
In some embodiments of the utility model, wing 50 further include: aileron rudder face 55 passes through aileron with wing 50
The both ends shaft of rudder face 55 connects；
In some embodiments of the utility model, enging cabin 40 further include: slab tail rudder face 41 and starts
Cabin 40 is connected by wing root shaft, and slab tail rudder face 41 and aileron rudder face 55 are complete sandwich multiple material structures, utilizes four pieces of rudders
The three axes control of unmanned plane is realized in the deflection in face (i.e. two pieces of aileron rudder faces 55 and two pieces of slab tail rudder faces 41)；Wherein, aileron
Rudder face 55 uses trailing edge monolithic rudder face, and empennage rudder face 41 is using dynamic vee tail entirely.
In some embodiments of the utility model, as shown in Figure 1, wing 50 includes: supersonic wing, angle of sweep is big
In 45 °, aspect ratio is less than 4；And long endurance wing, angle of sweep are not less than 4 no more than 45 °, aspect ratio；Supersonic wing and length
Endurance wing is two pairs of alternative wings, and the size positions of attachment lug and end face aerofoil profile on the connecting end surface of two pairs of wings are complete
It is complete consistent, it can replace mutually, according to aerial mission mounted in pairs on center fuselage cabin 30, supersonic wing is small using big sweepback
Aspect ratio delta wing configuration is, it can be achieved that the higher flying speed of high and medium；Long endurance wing uses the medium aspect ratio of medium and small sweepback
Tapered airfoil layout, it can be achieved that the longer endurance of high and medium, supersonic wing can realize the maximum flying speed of high and medium Ma1.8,
Cruising speed is Ma1.2, endurance 60min；Long endurance wing can realize the maximum flying speed of high and medium Ma1.2, cruise speed
Degree is Ma0.8, endurance 100min.
In some embodiments of the utility model, as shown in Figure 1, mission payload cabin 20 includes: to load corner reflector
First task cabin；Load the second mission module of high definition aerial camera；And load the third mission module of photoelectric nacelle, mission payload
Cabin 20 is the installation bay section of mission payload, and every kind of mission payload is all assembled into independence and the identical cabin of outer dimension before factory
Section, corresponding mission payload cabin 20 is selected before each aerial mission and carries out full machine assembling, copes with different flight to realize
Task.
In some embodiments of the utility model, the connecting end surface in center fuselage cabin 30 and mission payload cabin 20 is provided with
Aerospace connectors realize the communication and power supply of mission payload.
In some embodiments of the utility model, the connecting end surface in enging cabin 40 and center fuselage cabin 30 is provided with boat
Empty connector and cortex oil pipe quick connecting valve, for ECU, the fuel supply of the communication of empennage steering engine, power supply and engine.
In some embodiments of the utility model, the connecting end surface in wing 50 and center fuselage cabin 30 is provided with aviation company
Device is connect, the communication and power supply for equipment in aileron rudder face and center fuselage cabin 30.
The whole assembly signal of modularization supersonic speed unmanned plane (long endurance reconnaissance version) provided by the embodiment of the utility model
Figure is as shown in figure 4, fuselage uses high-fineness ratio (being greater than 12) body of revolution fuselage appearance, back S type air intake duct, using band boundary-layer
Main control, navigation, link and the Aerial Electronic Equipment of flying of two-dimentional ramp type air inlet every road, full machine is all mounted on mission payload cabin 20
In center fuselage cabin 30, fuel tank is located at immediate vicinity in center fuselage cabin 30, reduces because the full machine of oil consumption bring is longitudinal
Trim interference.
According to above description, those skilled in the art should to modularization supersonic speed provided by the embodiment of the utility model without
It is man-machine to have clear understanding.
In conclusion modularization supersonic speed unmanned plane provided by the embodiment of the utility model is by each main portion in unmanned plane
Part uses modular assembly, can quickly repair unmanned plane by replacing failure bay section, come into operation rapidly, mean failure rate reparation
Time greatly shortens, and flexibly, two sets of unmanned planes can realize redundancy backup and multipurpose flight, comprehensive coverage for Flight Line Maintenance maintenance
Equipment is lower with the system use cost unmanned plane for comparing many types of single task role.
It should also be noted that, the direction term mentioned in embodiment, for example, "upper", "lower", "front", "rear", " left side ",
" right side " etc. is only the direction with reference to attached drawing, is not used to limit the protection scope of the utility model.Through attached drawing, identical member
Element is indicated by same or similar appended drawing reference.When may cause the understanding to the utility model and cause to obscure, will omit
Conventional structure or construction.
And the shape and size of each component do not reflect actual size and ratio in figure, and only the utility model are illustrated to implement
The content of example.In addition, in the claims, any reference symbol between parentheses should not be configured to claim
Limitation.
Similarly, it should be understood that in order to simplify the utility model and help to understand one or more in each open aspect
A, in the description above to the exemplary embodiment of the utility model, each feature of the utility model is divided together sometimes
Group is into single embodiment, figure or descriptions thereof.However, the method for the disclosure should not be construed to reflect following meaning
Figure: the requires of the utility model features more more than feature expressly recited in each claim i.e. claimed.
More precisely, open aspect is less than single implementation disclosed above as claims of front reflect
All features of example.Therefore, it then follows thus claims of specific embodiment are expressly incorporated in the specific embodiment,
In separate embodiments of each claim as the utility model itself.
Particular embodiments described above has carried out into one the purpose of this utility model, technical scheme and beneficial effects
Step is described in detail, it should be understood that being not limited to this foregoing is merely specific embodiment of the utility model
Utility model, within the spirit and principle of the utility model, any modification, equivalent substitution, improvement and etc. done should all wrap
Containing being within the protection scope of the utility model.
Claims (10)
1. a kind of modularization supersonic speed unmanned plane characterized by comprising
Buffering energy-absorbing nose cone, contact to earth energy-absorbing when unmanned aircraft parachute descent lands, and protects housing construction and airborne equipment；
Mission payload cabin, front end are connect with the rear removable of the buffering energy-absorbing nose cone, interior to install mission payload；
Center fuselage cabin, front end are connect with the rear removable in the mission payload cabin, and electrical with the mission payload cabin
Connection, it is interior that airborne Aerial Electronic Equipment, recorery parachute and fuel tank are installed；
Enging cabin, front end are connect with the rear removable in the center fuselage cabin, and with the center fuselage cabin electrically with
Piping connection, interior installation turbojet, jet pipe and empennage；And
Wing, connecting end surface and the side in the center fuselage cabin are detachably connected, and are electrically connected with the center fuselage cabin
It connects.
2. modularization supersonic speed unmanned plane according to claim 1, which is characterized in that the buffering energy-absorbing nose cone with it is described
Between mission payload cabin, between the mission payload cabin and the center fuselage cabin and the center fuselage cabin is started with described
Cooperated between cabin using flange, and is detachably connected by radial bolts；
Wherein, shape for hat beam is provided on the enging cabin and the connecting end surface in the center fuselage cabin.
3. modularization supersonic speed unmanned plane according to claim 1, which is characterized in that wherein:
The center fuselage cabin includes:
Auricle before inside is set to the side in the center fuselage cabin；
Auricle behind inside is set to the side in the center fuselage cabin, with auricle before the inside along the center fuselage cabin
Axially spaced-apart setting；
The wing includes:
Auricle before outside is set to the connecting end surface of the wing Yu the center fuselage cabin, and can with auricle before the inside
Dismantling connection；
Auricle behind outside is set to the connecting end surface of the wing Yu the center fuselage cabin, with auricle edge before the outside
The tangential interval of the wing is arranged, and is detachably connected with auricle behind the inside.
4. modularization supersonic speed unmanned plane according to claim 3, which is characterized in that wherein:
Before the inside behind auricle and the inside auricle include: the first auricle being axially arranged along the center fuselage cabin and
Second auricle；
First auricle of auricle and second auricle are folded in front of the outside on the two sides of auricle before the inside；
First auricle of auricle and second auricle are folded in behind the outside on the two sides of auricle behind the inside.
5. modularization supersonic speed unmanned plane according to claim 4, which is characterized in that auricle before the inside, described outer
Be provided on auricle behind auricle and the outside behind auricle, the inside before side the first through hole arranged along the vertical direction and
Second through-hole；
Wherein:
The diameter of the first through hole of auricle is 12mm before auricle and the outside before the inside；
The diameter of second through-hole of auricle is 10mm before auricle and the outside before the inside；
The diameter of the first through hole of auricle is 8mm behind auricle and the outside behind the inside；
The diameter of second through-hole of auricle is 6mm behind auricle and the outside behind the inside.
6. modularization supersonic speed unmanned plane according to claim 5, which is characterized in that the wing and the center fuselage
The junction in cabin is provided with wing body rectification outer cover.
7. modularization supersonic speed unmanned plane according to claim 4, which is characterized in that wherein:
It is additionally provided in the wing:
Front-axle beam runs through beam to be I-shaped, through the entire wing；
The back rest is C font short beam, connect with the front-axle beam, and is arranged with the front-axle beam in y font；
Wherein, auricle is connect with the front-axle beam before the outside, and auricle is connect with the back rest behind the outside；
The center fuselage cabin further include:
Two ring frames, the axis setting of the ring frame surrounding said central fuselage compartment, and the axial direction along the center fuselage cabin
Interval setting；
Wherein, auricle is connect with two ring frames respectively behind auricle and the inside before the inside；
The wing further include: aileron rudder face is connect with the wing by the both ends shaft of the aileron rudder face；
The enging cabin further include: slab tail rudder face is connect with the enging cabin by wing root shaft；
Wherein, the slab tail rudder face and aileron rudder face are complete sandwich multiple material structure, realize nothing using the deflection of four pieces of rudder faces
Man-machine three axes control.
8. modularization supersonic speed unmanned plane according to claim 1, which is characterized in that the wing includes:
Supersonic wing, angle of sweep are greater than 45 °, and aspect ratio is less than 4；And
Long endurance wing, angle of sweep are not less than 4 no more than 45 °, aspect ratio.
9. modularization supersonic speed unmanned plane according to claim 1, which is characterized in that the mission payload cabin includes:
Load the first task cabin of corner reflector；
Load the second mission module of high definition aerial camera；And
Load the third mission module of photoelectric nacelle.
10. modularization supersonic speed unmanned plane according to claim 1, which is characterized in that wherein:
The company of the connecting end surface in the center fuselage cabin and the mission payload cabin, the enging cabin and the center fuselage cabin
Contact surface and the wing and the connecting end surface in the center fuselage cabin are provided with aerospace connectors；
The enging cabin and the connecting end surface in the center fuselage cabin are additionally provided with oil pipe quick connecting valve.
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| CN201821238245.8U CN208715479U (en) | 2018-08-02 | 2018-08-02 | Modularization supersonic speed unmanned plane |
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Cited By (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN108820204A (en) * | 2018-08-02 | 2018-11-16 | 中国科学院工程热物理研究所 | Modularization supersonic speed unmanned plane |
| CN110697018A (en) * | 2019-10-23 | 2020-01-17 | 彩虹无人机科技有限公司 | Unmanned aerial vehicle wing and fuselage connecting device |
| CN112407242A (en) * | 2020-11-09 | 2021-02-26 | 北京北航天宇长鹰无人机科技有限公司 | A connect integral root rib and unmanned aerial vehicle for unmanned aerial vehicle fin |
| WO2021139047A1 (en) * | 2020-01-09 | 2021-07-15 | 南京祖航航空科技有限公司 | Modular quick-to-disassemble unmanned aerial vehicle |
-
2018
- 2018-08-02 CN CN201821238245.8U patent/CN208715479U/en active Active
Cited By (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN108820204A (en) * | 2018-08-02 | 2018-11-16 | 中国科学院工程热物理研究所 | Modularization supersonic speed unmanned plane |
| CN110697018A (en) * | 2019-10-23 | 2020-01-17 | 彩虹无人机科技有限公司 | Unmanned aerial vehicle wing and fuselage connecting device |
| CN110697018B (en) * | 2019-10-23 | 2021-10-01 | 彩虹无人机科技有限公司 | Unmanned aerial vehicle wing and fuselage connecting device |
| WO2021139047A1 (en) * | 2020-01-09 | 2021-07-15 | 南京祖航航空科技有限公司 | Modular quick-to-disassemble unmanned aerial vehicle |
| CN112407242A (en) * | 2020-11-09 | 2021-02-26 | 北京北航天宇长鹰无人机科技有限公司 | A connect integral root rib and unmanned aerial vehicle for unmanned aerial vehicle fin |
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