CN112607014B - Combined system of manned machine and unmanned aerial vehicle - Google Patents
Combined system of manned machine and unmanned aerial vehicle Download PDFInfo
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- CN112607014B CN112607014B CN202011599938.1A CN202011599938A CN112607014B CN 112607014 B CN112607014 B CN 112607014B CN 202011599938 A CN202011599938 A CN 202011599938A CN 112607014 B CN112607014 B CN 112607014B
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Abstract
The application provides a combined system who has man-machine and unmanned aerial vehicle, combined system is including man-machine (1), first external unmanned aerial vehicle (2), second external unmanned aerial vehicle (3), preceding connector (4), wingtip connector (5), wherein: the manned machine (1) is provided with the nacelles in the middle of wings on two sides of the manned machine (1), and the nacelles on the two sides are respectively provided with a man-machine front coupler (4); the wingtips on the two sides of the horizontal tail of the manned aircraft (1) are respectively provided with a manned aircraft wingtip connector; the unmanned aerial vehicle front connector of the first externally hung unmanned aerial vehicle (2) and the unmanned aerial vehicle front connector of the second externally hung unmanned aerial vehicle (3) are respectively connected with the manned front connectors of the nacelles at two sides of the manned aircraft (1); the unmanned aerial vehicle wingtip coupler of the first externally hung unmanned aerial vehicle (2) and the unmanned aerial vehicle wingtip coupler of the second externally hung unmanned aerial vehicle (3) are respectively connected with manned wingtip couplers on two sides of the manned aircraft (1).
Description
Technical Field
The application relates to aircraft design, concretely relates to combined system who has man machine and unmanned aerial vehicle.
Background
The combination of man-machine and unmanned aerial vehicle is the direction of future aviation field development. The current manned/unmanned aerial vehicle combination mode generally adopts two modes of manned wing lower hanging unmanned aerial vehicle and fuselage internal cabin loading unmanned aerial vehicle. The former is constrained by factors such as hanging capacity of a hanging point under a wing, peripheral structure size of the hanging point and the like, and has high requirements on weight, geometric dimension, layout form and the like of the unmanned aerial vehicle; the latter has higher requirements on elements such as the weight, the geometric dimension, the cabin size of the unmanned aerial vehicle body and the like. Neither form has the mounting capability of a large/medium sized drone.
In order to meet the requirements of the aspects of height, voyage, endurance, load, reaction time, coverage area and the like, the existing man-machine/unmanned aerial vehicle combination scheme needs the airplane to obtain the balance between the self performance of the airplane and the performance of the unmanned aerial vehicle at the cost of certain aerodynamic drag loss or reduction of flight performance. In addition, unmanned aerial vehicle and someone must synchronous design, and commonality, adaptability and the expansion service ability of both are all lower, and hardly solve the control difficult problem that the pneumatic overall arrangement form difference of different configurations is too big to bring. The human-computer is used as a special unmanned-computer-mounted machine, and the self-use adaptability and universality are not strong.
Disclosure of Invention
In order to solve the technical problem, the combined system with the unmanned aerial vehicle is provided by the application, and the requirements are met by adopting a mode of combining an externally hung unmanned aerial vehicle with the unmanned aerial vehicle.
The application provides a combined system who has people's machine and unmanned aerial vehicle, combined system is including man-machine (1), first external unmanned aerial vehicle (2), second external unmanned aerial vehicle (3), preceding connector (4), wing tip connector (5), preceding connector (4) including before man-machine connector and the unmanned aerial vehicle connector, wing tip connector (5) including someone wing tip connector and unmanned aerial vehicle wing tip connector, wherein:
the manned aircraft comprises a manned aircraft body (1), wherein canard wings of the manned aircraft body (1) are retractable canard wings, the empennages are single vertical empennages, nacelles are arranged in the middles of wings on two sides of the manned aircraft body (1), the nacelles on the two sides are respectively provided with a man-machine front coupler (4), and the nacelles are used for accommodating an undercarriage and the front couplers (4); the wingtips on the two sides of the horizontal tail of the manned aircraft (1) are respectively provided with a manned aircraft wingtip connector;
the unmanned aerial vehicle front couplers are arranged at the positions of the machine heads of the first externally-hung unmanned aerial vehicle (2) and the second externally-hung unmanned aerial vehicle (3), and the unmanned aerial vehicle front coupler of the first externally-hung unmanned aerial vehicle (2) and the unmanned aerial vehicle front coupler of the second externally-hung unmanned aerial vehicle (3) are respectively connected with the manned front couplers of the nacelles at two sides of the manned aircraft (1); the outer edges of the wings of the first externally hung unmanned aerial vehicle (2) and the second externally hung unmanned aerial vehicle (3) are provided with unmanned aerial vehicle wing tip couplers, and the unmanned aerial vehicle wing tip couplers of the first externally hung unmanned aerial vehicle (2) and the unmanned aerial vehicle wing tip couplers of the second externally hung unmanned aerial vehicle (3) are respectively connected with manned wing tip couplers on two sides of the manned aircraft (1).
Preferably, the front coupler (4) and the wing tip coupler (5) are synchronously opened/closed and separated through an onboard computer.
Preferably, both the front coupling (4) and the wing tip coupling (5) have data transmission setting capability.
Preferably, the vertical tail wings of the first externally-hung unmanned aerial vehicle (2) and the second externally-hung unmanned aerial vehicle (3) are arranged at the wingtips of the horizontal tail wings and can be folded and folded together with the horizontal tail wings.
Preferably, the first externally-hung unmanned aerial vehicle (2) and the second externally-hung unmanned aerial vehicle (3) are folded inwards and upwards in a mounting state, and released to a horizontal state in a free flight state.
Preferably, the wings of the first externally hung unmanned aerial vehicle (2) and the second externally hung unmanned aerial vehicle (3) are straight wings or variable swept wings.
Preferably, the wings of the first externally-hung unmanned aerial vehicle (2) and the second externally-hung unmanned aerial vehicle (3) are straight wings, so that the outer sections of the wings can be retracted inwards to the inner wing sections in the mounting state of the first externally-hung unmanned aerial vehicle (2) and the second externally-hung unmanned aerial vehicle (3), and extend outwards to the complete state in the free flight state.
Preferably, the wing with the airplane (1) is a high-lift wing type under the condition of low Reynolds number.
To sum up, compare with the layout form of carrying unmanned aerial vehicle under the manned wing that the conventionality adopted or hanging unmanned aerial vehicle in the cabin, this layout scheme adopts the outside unmanned aerial vehicle mode of carrying on, has constituted the layout structure who is similar to two tail support tail forms when man-machine and unmanned aerial vehicle built-up connection, then forms normal aircraft layout form separately after the separation, has possessed following advantage:
1. the limited mounting capacity under the wing is saved, the unmanned aerial vehicle can be combined and matched with various weight grades and various layout forms on the premise of not influencing the self layout and mounting capacity of the unmanned aerial vehicle, and the combining capacity of the unmanned aerial vehicle and the manned aircraft is improved;
2. the manned aircraft adopts retractable duck wings which are used for adapting to the influence of attitude difference and instantaneous change of a combined system on the maneuvering performance when the unmanned aircraft is hung or separated;
3. the double-tail-support layout mode formed in the combined state can effectively improve the whole cruising speed, enlarge the use range of the unmanned aerial vehicle, improve the response time to sensitive events and sensitive targets, and reduce the resistance loss caused by the unmanned aerial vehicle serving as an external hanging object;
4. on the premise of not changing the overall layout form, the types of the unmanned aerial vehicles can be changed according to task requirements, various collocation modes (such as the unmanned aerial vehicles serving as ground missiles, baits, scouting and batting integrated machines, battlefield information base stations, battlefield monitoring equipment and the like) are realized, and the use adaptability and flexibility of the unmanned aerial vehicles are improved;
5. when the unmanned plane takes off with larger weight, the unmanned plane can be used as a boosting rocket, and the engine of the unmanned plane is used for providing auxiliary power, so that the integral taking-off and landing performance is improved;
6. the human-computer and unmanned aerial vehicle can complete upgrading and transformation without excessive modification, and the upgrading and transformation cost is low.
Drawings
Fig. 1 is a schematic view of a combined system of a human machine and an unmanned machine in a combined state according to the present application;
fig. 2 is a schematic diagram of a combined system of a human machine and an unmanned aerial vehicle provided in the present application in a separated state;
wherein: 1-man-machine, 2-first externally hung unmanned aerial vehicle, 3-second externally hung unmanned aerial vehicle, 4 front couplers and 5 wingtip couplers.
Detailed Description
Example one
The combined layout of the manned machine and the unmanned machine constructed by the invention has the advantages of flexible configuration, mature scheme, small constraint on the manned machine, small performance loss of the manned machine/unmanned machine, small difficulty in pneumatic conversion of different configurations and the like.
As shown in fig. 1-2, the present application provides a combined system of a manned machine and an unmanned machine, which comprises a manned machine (1 frame) and an unmanned machine (2 frames).
The man-machine adopts a normal layout, a built-in single-engine (or double-engine) is arranged in the machine body (or is hoisted below), and a retractable duck wing and a single vertical tail wing are adopted; the wing adopts a high-lift airfoil profile under a low Reynolds number. The rear edges of the front wing and the rear wing are provided with control surfaces, and the middle part of the wing is provided with a nacelle for accommodating an undercarriage and a front coupler of the unmanned aerial vehicle.
The unmanned aerial vehicle adopts straight wings, the outer sections of the wings can be retracted inwards to the inner wing sections in a mounting state, the outer sections of the wings extend outwards to a complete state in a free flight state, and the trailing edges of the wings are provided with control surfaces; the horizontal tail wing in the mounted state can be folded inwards and upwards and retracted, and is released to the horizontal state in the free flight state, the rear edge of the horizontal tail is provided with an operation control surface, and the elevator function is realized through deflection combination in different directions; the vertical tail wing is arranged at the wingtip of the horizontal tail wing and can be folded together with the horizontal tail wing, and the rear edge of the vertical tail wing is provided with an operation control surface to realize the function of a rudder through deflection in different directions; the engine is disposed at the rear upper side of the body (or inside the body).
The unmanned machine and the unmanned machine adopt a two-point connection mode, the nose of the unmanned machine and the rear part of the manned machine wing nacelle are front connection points, the wing tip of the unmanned machine wing and the horizontal tail wing tip of the manned machine are side connection points, and the two connection points realize synchronous opening/closing and separation through an onboard computer; the connecting point has data transmission setting capacity.
Example two
One embodiment of the invention is a combined attack system of a certain manned attack machine and an unmanned aerial vehicle. Specifically, including man-machine (1), unmanned aerial vehicle (2). The unmanned aerial vehicle adopts normal mode overall arrangement, adopts retractable duck wing, and the wing middle part sets up the nacelle and is used for accomodating undercarriage and unmanned aerial vehicle front coupling. The unmanned aerial vehicle adopts a straight retractable wing, and the outer section of the wing can be retracted inwards to the inner section of the wing; the horizontal rear wing can be folded, retracted, extended and released. The unmanned aerial vehicle aircraft nose and manned aircraft wing nacelle, unmanned aerial vehicle wing wingtip and manned aircraft horizontal tail wingtip two-point connection mode, two connection points can realize the synchronous connection/separation; the connecting point has data transmission setting capacity.
The length of the man-machine is 12m, the wingspan is 15.5m, the height of the man-machine is 4.3m, and the reference area of the wing is 60 square meters. The unmanned aerial vehicle has the advantages of 5.38m of length, 6.2m (full extension)/3.2 m (full retraction) of wingspan, 1.2m of height and 20 square meters of wing reference area.
Through calculation and analysis, the performance indexes which can be achieved by the embodiment are as follows:
maximum airspeed Ma =1.0 (unmanned only)/0.4 (unmanned only)/0.8 (combined state);
standby speed Ma =0.7 (standalone drone)/0.1 (standalone drone)/0.6 (combined state);
standby height 8000m (individual man machine)/2500 m (individual unmanned machine)/5000 (combination state);
endurance (R =800 km) 6h (unmanned only)/3 h (unmanned only)/4.5 h (combined state);
the maximum range is 3000km (unmanned alone)/800 km (unmanned alone)/1500 km (combined status).
To sum up, the combined system who has people's machine and unmanned aerial vehicle that this application provided, by 1 combination overall arrangement that people's machine and 2 unmanned aerial vehicles front and back connections formed. The unmanned aerial vehicle wing nacelle is connected with an unmanned aerial vehicle head, and the unmanned aerial vehicle wing tip is connected with the manned horizontal tail wing tip in a two-point connection mode; the two connecting points can realize synchronous connection/separation; the connecting point has data transmission setting capacity.
Claims (2)
1. The utility model provides a combined system who has people's machine and unmanned aerial vehicle, its characterized in that, combined system is including man-machine (1), first external unmanned aerial vehicle (2), second external unmanned aerial vehicle (3), preceding connector (4), wing tip connector (5), preceding connector (4) are including the connector before man-machine preceding connector and unmanned aerial vehicle, wing tip connector (5) are including someone wing tip connector and unmanned aerial vehicle wing tip connector, wherein:
the canard wing with the manned machine (1) adopts a retractable canard wing, the empennage is a single vertical empennage, the middles of wings on two sides of the manned machine (1) are respectively provided with a nacelle, the nacelles on the two sides are respectively provided with a man-machine front coupler (4), and the nacelle is used for accommodating an undercarriage and the front couplers (4); the wingtips on two sides of the horizontal tail of the manned aircraft (1) are respectively provided with a manned wingtip coupler;
the unmanned aerial vehicle front couplers of the first externally hung unmanned aerial vehicle (2) and the second externally hung unmanned aerial vehicle (3) are arranged at the machine head positions of the first externally hung unmanned aerial vehicle (2) and the second externally hung unmanned aerial vehicle (3), and are respectively connected with the manned machine front couplers of the nacelles at the two sides of the manned machine (1); unmanned aerial vehicle wing tip couplers are arranged at the outer edges of wings of the first externally hung unmanned aerial vehicle (2) and the second externally hung unmanned aerial vehicle (3), and the unmanned aerial vehicle wing tip coupler of the first externally hung unmanned aerial vehicle (2) and the unmanned aerial vehicle wing tip coupler of the second externally hung unmanned aerial vehicle (3) are respectively connected with manned wing tip couplers at two sides of the manned aircraft (1);
the vertical tail wings of the first externally hung unmanned aerial vehicle (2) and the second externally hung unmanned aerial vehicle (3) are arranged at the wingtips of the horizontal tail wings and can be folded together with the horizontal tail wings;
the first externally hung unmanned aerial vehicle (2) and the second externally hung unmanned aerial vehicle (3) are folded inwards and upwards in a horizontal tail wing in a mounting state and released to a horizontal state in a free flight state;
the wings of the first externally-hung unmanned aerial vehicle (2) and the second externally-hung unmanned aerial vehicle (3) are flat wings, at the moment, the outer sections of the wings of the first externally-hung unmanned aerial vehicle (2) and the second externally-hung unmanned aerial vehicle (3) can be retracted inwards to the inner wing sections in a mounted state, and the outer sections of the wings of the first externally-hung unmanned aerial vehicle (2) and the second externally-hung unmanned aerial vehicle (3) extend outwards to a fully-unfolded state in a free flight state;
the front coupler (4) and the wing tip coupler (5) are synchronously coupled and separated through an airborne computer;
both the front coupling (4) and the wingtip coupling (5) have data transmission capabilities.
2. Combination system according to claim 1, wherein the wing with the aircraft (1) is a high lift airfoil at low reynolds number.
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