CN214057884U - Combined aircraft layout - Google Patents
Combined aircraft layout Download PDFInfo
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- CN214057884U CN214057884U CN202022128099.7U CN202022128099U CN214057884U CN 214057884 U CN214057884 U CN 214057884U CN 202022128099 U CN202022128099 U CN 202022128099U CN 214057884 U CN214057884 U CN 214057884U
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Abstract
The utility model belongs to the technical field of the aerodynamic appearance design of an aircraft, and discloses a combined aircraft layout and connecting mechanism, which comprises a main machine and two sub machines, wherein the main machine and the sub machines are both in flying wing layout; the planar shapes of the main machine and the sub machine are consistent, and the main machine and the sub machine are both provided with a single front edge and a single rear edge; the two submachine are arranged at two sides of the rear edge of the main machine, and the front edge of the submachine is connected with the rear edge of the main machine; the front edge sweepback angles of the main machine and the sub machine are the same. The utility model discloses a combination aircraft has the characteristic that aerodynamic performance is good, high stealthy and high lift-drag ratio concurrently, can realize long-range operation functions such as putting in, the aerial network deployment of parasite aircraft, has effectively extended the function of aircraft, has improved the operation effect of aircraft.
Description
Technical Field
The utility model discloses the aerodynamic appearance of aircraft designs technical field, especially relates to a combination aircraft overall arrangement.
Background
The combined aircraft is a novel aircraft design concept. The combined aircraft combines various aircrafts with different functions into a whole to fly cooperatively, thereby realizing function optimization and achieving the purpose of specific battle. The combined aircraft realizes the function aggregation of aircrafts with different functions, and the high-speed remote function of the host machine is utilized to realize that submachine quickly reaches a combat area to form the situation of low-cost unmanned aerial vehicle cooperative combat; the combined aircraft can realize the function of changing one aircraft into multiple aircraft during air combat, form the air cluster combat capability, break through the air defense capability of enemies, and further improve the combat efficiency.
The conventional combined aircraft mostly adopts a mode of connecting the wingtips with the wingtips, the bending moment is large, and the difficulty is large in structural design.
SUMMERY OF THE UTILITY MODEL
The utility model discloses it is providing a combination aircraft overall arrangement to when solving current combination aircraft and adopting wingtip and wingtip to be connected, the moment of flexure is great, the big problem of the structural design degree of difficulty.
In order to achieve the above purpose, the utility model provides a following technical scheme: a combined aircraft layout comprises a host machine and two sub machines, wherein the host machine and the sub machines are both in flying wing layout; the planar shapes of the main machine and the sub machine are consistent, and the main machine and the sub machine are provided with a single front edge and a single rear edge; the two submachine are arranged at two sides of the rear edge of the main machine, and the front edge of the submachine is connected with the rear edge of the main machine; the front edge sweepback angles of the main machine and the sub machine are the same.
Further, the back sweep angle of the front edge of the main machine and the back sweep angle of the sub machine are the same as the back edge of the main machine and the back sweep angle of the sub machine.
Further, the length of the sub machine is half of that of the main machine.
Further, the tail part of the main machine is provided with a V-shaped tail wing, the range of the outward turning angle of the V-shaped tail wing is 30-45 degrees, and the tail part of the submachine is provided with a vertical tail.
Furthermore, the V-shaped tail wing of the main machine is provided with a reinforcing cross beam, and a supporting cross beam is connected between the vertical tail of the sub machine and the V-shaped tail wing of the main machine.
Further, the sweep angle of the front edge of the main machine and the sub machine is 40-50 degrees.
To sum up, owing to adopted above-mentioned technical scheme, the beneficial effects of the utility model are that: the main machine and the sub machine of the combined aircraft adopt flying wing layout, have the characteristics of good pneumatic performance and high stealth, and can improve the overall stealth performance of the combined aircraft; in addition, the shapes of the main machine and the sub machine are consistent, the length of the sub machine is half of that of the main machine, the front edge sweepback angles of the main machine and the sub machine are the same, the front edge sweepback angles are the same as the rear edge sweepback angles thereof and are similar to rhombus, but the sizes are different, and the lift-drag ratio of the whole machine can be obviously improved by the combination; meanwhile, the V-shaped tail wing of the main machine is provided with a reinforcing cross beam, and the vertical tail of the sub machine is connected with the V-shaped tail wing of the main machine through a supporting cross beam, so that a structural connection mode of adding one line at one point is formed, compared with the point connection of the existing combined aircraft, the structural strength is improved, and the safety in the flight process is ensured. The utility model discloses a combination aircraft make full use of the long-range advantage that can consume with the low-cost of parasite aircraft of host computer speed height, aircraft pneumatic performance after the combination obviously increases, can realize long-range operation functions such as throwing in, the aerial network deployment of parasite aircraft, has effectively extended the function of aircraft, improves the operation effect of aircraft.
Drawings
Fig. 1 is a schematic layout plan view of a layout of a combined aircraft according to an embodiment of the present invention;
fig. 2 is a layout oblique view of a layout of a combined aircraft according to a first embodiment of the present invention;
fig. 3 is a schematic design diagram of a leading edge sweepback angle of a combined aircraft layout according to an embodiment of the present invention;
fig. 4 is a layout schematic diagram of a layout of a combined aircraft provided in the second embodiment of the present invention;
fig. 5 is a layout schematic diagram of a combined aircraft layout provided by the third embodiment of the present invention
Detailed Description
The invention will be described in further detail with reference to the following drawings and embodiments:
reference numerals in the drawings of the specification include: the device comprises a main machine 1, a sub machine 2, a V-shaped tail wing 3, a vertical tail 4, a reinforcing cross beam 5 and a supporting cross beam 6.
Example one
As shown in fig. 1, 2 and 3, a combined aircraft layout comprises a main machine 1 and two sub machines 2, wherein both the main machine 1 and the sub machines 2 adopt flying wing layouts; the plane shapes of the main machine 1 and the sub machine 2 are consistent, the length of the sub machine 2 is half of that of the main machine 1, and the main machine 1 and the sub machine 2 are both provided with a single front edge and a single rear edge; the two sub machines 2 are arranged at two sides of the rear edge of the main machine 1, and the front edges of the sub machines 2 are connected with the rear edge of the main machine 1 to be used as a first connecting mechanism of the sub machines 2; the front edge sweepback angles of the main machine 1 and the sub machine 2 are the same, and the front edge sweepback angles of the main machine 1 and the sub machine 2 are the same as the rear edge sweepback angles of the main machine 1 and the sub machine 2, so that the connection performance of the main machine 1 and the sub machine 2 is ensured, and the stealth performance and the pneumatic performance of the combined aircraft are considered at the same time.
Aiming at the flight requirements of different combined aircrafts for supersonic cruise, the leading edge sweepback angles of the main machine 1 and the submachine 2 can be specially designed according to the flight Mach number, and in order to reduce the shock resistance of the main machine 1, the leading edge sweepback angle of the main machine 1 needs to satisfy the following relational expression:
the back sweep angle of the front edge of the main machine 1 and the sub machine 2 is 40-50 degrees.
When the leading edge sweepback angle is 40 degrees, the aspect ratio of the main engine 1 is 2.363, and the aspect ratio of the combined aircraft is 3.5467; when the sweepback angle is 45 degrees, the aspect ratio of the main engine 1 is 2, and the aspect ratio of the combined aircraft is 3.0; when the sweep angle is 50 degrees, the aspect ratio of the main engine 1 is 1.6764, and the aspect ratio of the combined aircraft is 2.5147. The aspect ratio of the main machine 1 and the sub machine 2 is the same, and the aspect ratio of the combined aircraft is 1.5 times of that of the main machine 1. When the flying Ma is 0.75, the sweep angle is in the range of 40-50 degrees, and the maximum lift-drag ratio of the combined aircraft is improved by about 5 points compared with that of the single main engine 1.
The layout has the characteristics of high lift-drag ratio and high stealth, the structure is simple, and the host machine 1 and the sub machine 2 are convenient to separate.
Example two
As shown in fig. 4, the difference between the second embodiment and the first embodiment is that the V-shaped tail 3 is arranged at the tail of the main machine 1, the eversion angle of the V-shaped tail 3 ranges from 30 degrees to 45 degrees, the vertical tail 4 is arranged at the tail of the sub machine 2, the V-shaped tail 3 can increase the lateral stability of the flying wing layout, and the V-shaped tail 3 is provided with a rudder which provides a heading and a rolling moment for the combined aircraft when the rudder deflects to one direction at the same time. When the rudder deflects in the opposite direction, a pitching moment can be provided for the aircraft.
The main machine 1 adopts a V-shaped tail wing 3 to meet the requirements of lateral stability and control, and the sub machine 2 adopts a vertical tail 4 to meet the requirements of lateral stability and control.
EXAMPLE III
As shown in fig. 5, the difference between the third embodiment and the second embodiment is that, because the distance between the center of gravity of the handset 2 and the connecting position is relatively long, if the center of gravity of the handset 2 is at 50% of the length of the body of the handset 2, the moment arm generated by the weight of the handset 2 reaches 0.5 · l2cos (X) (where l)2χ is a leading-edge sweep angle for the length of the sub-machine 2) and thus brings a moment of a large weight of the sub-machine 2, a certain deformation of the sub-machine 2 is generated in the vertical direction.
In order to improve the structural strength and the safety of the combined aircraft, the V-shaped empennage 3 of the main machine 1 is provided with the reinforcing beam 5, so that on one hand, the structural strength of the connection between the V-shaped empennage 3 and the main machine 1 can be improved, and on the other hand, the reinforcing beam 5 can serve as a horizontal tail to provide pitching operation torque for the aircraft.
A supporting beam 6 is connected between the vertical tail 4 of the sub machine 2 and the V-shaped tail 3 of the main machine 1 and is used as a second connecting mechanism of the sub machine 2. Therefore, the connection between the sub machine 2 and the main machine 1 is changed into the joint stress connection of the tail part and the front edge, the structural strength of the system can be increased, and the single-edge hanging deformation of the sub machine 2 can be avoided.
This kind of overall arrangement is similar with conventional unmanned aerial vehicle, has obvious horizontal tail, vertical tail part, and this kind of structure has intensity height, the security is good, stability is good, characteristics such as control convenience.
The above description is only an example of the present invention, and the detailed technical solutions and/or characteristics known in the solutions are not described too much here. It should be noted that, for those skilled in the art, without departing from the technical solution of the present invention, several modifications and improvements can be made, which should also be regarded as the protection scope of the present invention, and these will not affect the effect of the implementation of the present invention and the practicability of the patent. The scope of the claims of the present application shall be determined by the contents of the claims, and the description of the embodiments and the like in the specification shall be used to explain the contents of the claims.
Claims (6)
1. A composite aircraft layout, characterized by: the aircraft wing aircraft comprises a main machine and two sub machines, wherein the main machine and the sub machines are both in flying wing layout; the planar shapes of the main machine and the sub machine are consistent, and the main machine and the sub machine are provided with a single front edge and a single rear edge; the two submachine are arranged at two sides of the rear edge of the main machine, and the front edge of the submachine is connected with the rear edge of the main machine; the front edge sweepback angles of the main machine and the sub machine are the same.
2. A combination aircraft layout according to claim 1, characterized in that: the front edge sweepback angles of the main machine and the sub machine are the same as the rear edge sweepback angles of the main machine and the sub machine.
3. A combined aircraft layout according to claim 2, characterized in that: the length of the sub machine is half of that of the main machine.
4. A combined aircraft layout according to claim 3, characterized in that: the tail of the main machine is provided with a V-shaped tail wing, the outward-turning angle of the V-shaped tail wing is 30-45 degrees, and the tail of the submachine is provided with a vertical tail.
5. A combined aircraft layout according to claim 4, characterized in that: the V-shaped tail wing of the main machine is provided with a reinforcing cross beam, and a supporting cross beam is connected between the vertical tail of the sub machine and the V-shaped tail wing of the main machine.
6. A combined aircraft layout according to any of claims 1 to 5, characterized in that: the back sweep angle of the front edge of the main machine and the sub machine is 40-50 degrees.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202022128099.7U CN214057884U (en) | 2020-09-25 | 2020-09-25 | Combined aircraft layout |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202022128099.7U CN214057884U (en) | 2020-09-25 | 2020-09-25 | Combined aircraft layout |
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| CN214057884U true CN214057884U (en) | 2021-08-27 |
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| CN202022128099.7U Active CN214057884U (en) | 2020-09-25 | 2020-09-25 | Combined aircraft layout |
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Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN112093026A (en) * | 2020-09-25 | 2020-12-18 | 中国空气动力研究与发展中心 | Combined aircraft layout and connecting mechanism |
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Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN112093026A (en) * | 2020-09-25 | 2020-12-18 | 中国空气动力研究与发展中心 | Combined aircraft layout and connecting mechanism |
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