CN204822081U - Nearly spacecraft with dirigible and ornithopter - Google Patents
Nearly spacecraft with dirigible and ornithopter Download PDFInfo
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- CN204822081U CN204822081U CN201520438305.0U CN201520438305U CN204822081U CN 204822081 U CN204822081 U CN 204822081U CN 201520438305 U CN201520438305 U CN 201520438305U CN 204822081 U CN204822081 U CN 204822081U
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- dirigible
- wing
- flapping
- near space
- wing aircraft
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Abstract
The utility model discloses a nearly spacecraft with dirigible and ornithopter, dirigible (1) and the ornithopter of sub -unit connection including upper portion. Dirigible (1) is including hull (12) to and be located the perpendicular stabilizing surface of dirigible (9) and the horizontal stabilizing surface of dirigible (10) of hull (12) afterbody. Dirigible (1) surface is equipped with solar cell panel. The ornithopter wing is combined material, can adopt tapered airfoil, the straight wing, dalta wing or bionical wing structure. The utility model discloses mainly provide lift by the dirigible to can provide the partial propulsive force and the power of manipulation. Mainly provide the propulsive force and the power of manipulation by ornithopter to can provide partial lift. It is long through its high altitude dwell time who has the dirigible of combination between them messenger, but the outstanding performance of short distance VTOL has the flight speciality that aircraft mobility is strong, the navigability is strong, the flight stability is good simultaneously concurrently.
Description
Technical field
The utility model relates to a kind of nearly aircraft, and especially relate to a kind of aircraft can carrying out detection at space or near space, it has the dual characteristics of dirigible and flapping-wing aircraft, is suitable as near space vehicle or Mars probes.
Background technology
Near space is the spatial domain of span ground 20 ~ 100km, the development and application values that this region is important in communication support, information acquisition, electronic suppress etc.Near space field, can be divided into 3 levels by height: (1) low layer near space (20 ~ 30km), comprises from convective zone to stratospheric a part of spatial domain.(2) middle level near space (30 ~ 70km), comprises advection layer and interlayer spatial domain.(3) distal layer near space (>70km), comprises interlayer and a part of thermosphere spatial domain.Near space field and outer space environment environment are complicated, and in this spatial domain, density of air is lower, and traditional aerospace vehicle is difficult to carry out in this space permanently effective flight and resident, and the flying instrument therefore developed near space and deep space probing is significant.
Tradition Near Space Flying Vehicles can be divided into two classes by its flying speed: (1) low speed Near Space Flying Vehicles, and (2) high speed Near Space Flying Vehicles consists predominantly of balloon, dirigible, unmanned plane, flapping-wing aircraft and with hypersonic aircraft etc.Wherein, dirigible and balloon can be detained for a long time by empty 30 kms on earth, but its be flexible body, volume is large, inertia is large, speed is slow, time-lag effect is remarkable.From fly to landing, external environment changes greatly, and be the temperature traverse and keep profile of conforming, it needs often inflation, venting, quality and centroid position variation frequent, manipulative capability is poor, and therefore practical application design is upper exists larger difficulty.And on the other hand, based on the aircraft of unmanned plane and hypersonic vehicle, they have outstanding manipulative capability and stability, but flight cost higher being also difficult to carries out permanently effective flight and resident at Near Space Flying Vehicles, therefore design still exists larger difficulty.In addition, how to provide sustainable stable power resources, improve flight maneuver, alerting ability and viability are that Near Space Flying Vehicles becomes the significant challenge of long-time main flow aircraft near space.
Utility model content
The purpose of this utility model is the deficiency for traditional Near Space Flying Vehicles, there is provided one can have flying for long time, resident under the rarefied air such as near space and outer space environment, there is high maneuverability, high flexibility, failure-survival capability, low energy consumption and good manipulative capability, stability, Near Space Flying Vehicles simultaneously with low cost.
For solving above technical matters, the technical scheme that the utility model adopts is: a kind of Near Space Flying Vehicles with dirigible and flapping-wing aircraft, the flapping-wing aircraft that the dirigible comprising top is connected with bottom.
Further, described dirigible comprises hull, and is positioned at dirigible fin and the dirigible horizontal stabilizer of submarine tail.
Further, described flapping-wing aircraft comprises airframe, and is arranged at the front wing of airframe and rear wing.
Further, dirigible surface is provided with solar panel.
Further, flapping-wing aircraft wing is composite material, can adopt tapered airfoil, the straight wing, delta wing or bionical wing structure.
Further, also comprise a connecting device, described dirigible is connected by described connecting device with flapping-wing aircraft, easy disassembly and maintenance.
Described flapping-wing aircraft its wing in flight course can have to comprise flutters, waves pendulum, reverses and flexible etc. multiple degree of freedom motions, can provide various state of flight thus, can adapt to the aerial mission in multiple situation.Described aircraft propulsive effort and actuating force can be provided by wing completely, and consume energy low, capacity usage ratio is high simultaneously.
Compared with prior art, the utility model possesses following advantage:
The Near Space Flying Vehicles such as traditional dirigible and unmanned plane need to carry enough fuel could provide lasting power for it, not only increase flight cost and further increase design difficulty, and conventional aircraft is difficult to the flight condition adapting to the various complexity of near space, lacks maneuverability and viability.And the utility model adopts dirigible to add the novel layouts form of flapping-wing aircraft, compensate for single dirigible or the flapping-wing aircraft deficiency as Near Space Flying Vehicles.It mainly provides lift by dirigible, and can provide part propulsive force and actuating force.Mainly provide propulsive force and actuating force by flapping-wing aircraft, and providing unit can divide lift.The high-altitude length of the halt being made it have dirigible by both combinations is long, can the excellent in performance of short distance vertical takeoff and landing, and have air maneuver concurrently strong, manipulative capability is strong, the flight speciality that flight stability is good simultaneously.
The energy that the power system of dirigible and flapping-wing aircraft can be carried by dirigible and flapping wing or the solar panel being laid on dirigible surface provide, flapping-wing aircraft energy consumption is low, capacity usage ratio is high, therefore permanent actuating force and propulsive effort can be provided, and flapping wing wing can carry out the motion of four degree of freedom, there is high maneuverability and powerful viability.
Technical advantage of the present utility model is, existing dirigible designing technique and flapping-wing aircraft designing technique can be utilized to carry out design of the present utility model, will be more convenient on manufacturing and designing.Aircraft technology and airship technology are organically combined, gives full play to both advantageous characteristics, maximize favourable factors and minimize unfavourable ones.Aircraft adopts flapping-wing aircraft form simultaneously, further enhances the flying power near space region and viability thereof.Can find out, the aircraft that the utility model patent proposes is a kind of high energy efficiency, high performance-price ratio, fully feasible scheme.
Accompanying drawing explanation
Fig. 1 is the structural representation of the utility model Near Space Flying Vehicles;
Fig. 2 is the structural representation of another preferred embodiment of the utility model Near Space Flying Vehicles;
Fig. 3 is the structural representation of the 3rd preferred embodiment of the utility model Near Space Flying Vehicles;
Fig. 4 is the lateral plan of the 3rd preferred embodiment of the utility model Near Space Flying Vehicles;
Fig. 5 is the A type flapping-wing aircraft of the utility model Near Space Flying Vehicles and the structural representation of connecting device;
Fig. 6 is the structural representation of the Type B flapping-wing aircraft of the utility model Near Space Flying Vehicles.
In figure:
1, dirigible; 2, A type flapping-wing aircraft; 3, wing
4, A type airframe 5, Type B flapping-wing aircraft 6, front wing;
7, rear wing; 8, Type B airframe; 9, dirigible fin;
10, dirigible horizontal stabilizer; 11, connecting device; 12, hull.
Detailed description of the invention
Below in conjunction with embodiment, embodiment of the present utility model is further described.
Embodiment 1:
The Near Space Flying Vehicles that this embodiment proposes have employed dirigible 1 as shown in Figure 1 and A type flapping-wing aircraft 2 combination, makes up single dirigible or the flapping-wing aircraft deficiency as Near Space Flying Vehicles while playing respective flight advantage.
The preferred rigid airship structural shape of dirigible 1 structure, dirigible 1 is a huge stream line pattern hull 12, be positioned at hull 12 afterbody and play the dirigible fin 9 of stability contorting effect by horizontal and vertical and dirigible horizontal stabilizer 10 forms, mainly dirigible 1 is played to the effect of stabilized flight.
Dirigible 1 surface is equipped with solar panel to provide power.
A type flapping-wing aircraft 2, comprises A type airframe 4 and wing 3, and wing 3 is connected by articulated mounting with A type airframe 4, and wing 3 can rotate around A type airframe 4, flutters up and down, thus produces lift, propulsive force and actuating force.
Flapping wing adopts lightweight structural material, bionic structure material or intellectual material, preferentially adopts composite structure, improves structure efficiency, and have integrated model simple, weight is less, maneuverable feature.
Embodiment 2:
As shown in Figure 2 and Figure 6, the basis of former embodiment 1 is replaced flapping-wing aircraft, the Type B flapping-wing aircraft 5 that it adopts comprises Type B airframe 8, front wing 6 and rear wing 7.
Type B flapping-wing aircraft 5 adopts imitative insect distribution form, form class is like dragonfly or fly structure, its front wing 6 and rear wing 7 can carry out quick and various motion, can produce the local instability's air-flow being different from ambient atmosphere completely, this unsteady aerodynamics effect is the important foundation realizing bionical flight.
Embodiment 3:
As shown in Figure 3-Figure 5, it adds a connecting device 11 on the basis of former embodiment 1 and embodiment 2, conveniently replaced, is convenient to change applicable model and care and maintenance.
The utility model provides a kind of Near Space Flying Vehicles of novel flight distribution form, by the version in conjunction with dirigible 1 and flapping-wing aircraft, make up single dirigible or flapping-wing aircraft as the deficiency of Near Space Flying Vehicles, make it have outstanding road-holding property and stability.Aircraft realizes taking off by the comparatively lift that dirigible 1 provides, dirigible 1 also can provide part propulsive force and actuating force simultaneously, there is provided enough propulsive forces and actuating force to realize pulsation-free by flapping-wing aircraft to rise, the buoyancy of dirigible 1 self can be utilized simultaneously to realize arriving the object of near space.
When aircraft resides in superaltitude, ornithopter type flight difficulty, now hover for a long time in spatial domain by top dirigible 1, when needs accelerate, turn to time, provide enough actuating forces by flapping-wing aircraft.Meanwhile, because flapping-wing aircraft wing can carry out multivariant motions such as fluttering, wave pendulum, reverse and stretch, make aircraft have very strong actuating force and alerting ability, diversified flight condition can be adapted to, there is powerful viability.And flapping-wing aircraft adopts biomimetic features, has low energy consumption, the feature that efficiency is high, aircraft flying for long time can be made, reduce flight cost, decrease environmental pollution, the near space that visible the utility model is applicable to entirely circumstance complication is changeable carries out long-term high-altitude flight.
The utility model has traditional near space device---the effect that balloon, dirigible, unmanned plane etc. do not have and advantage, it is made to be applicable to need the task of long-time low-speed operations, as patrol, exploration, search is just raw, advertisement photography, more makes it have development potentiality in many-sides such as near space communication support, information acquisition, electronic suppress, early warning.Unique bionic flapping-wing form has ensured its powerful actuating force, alerting ability, low energy consumption, dynamical power system further increase its flying power and viability, simultaneously the utility model aircraft flight cost is cheaper, allows it have as satellite or the outer space aircraft advantage that other aircraft do not have.
The content that above-described embodiment is illustrated should be understood to these embodiments only for being illustrated more clearly in the utility model, and be not used in restriction scope of the present utility model, after having read the utility model, the amendment of those skilled in the art to the various equivalent form of value of the present utility model has all fallen within the application's claims limited range.
Claims (6)
1. there is a Near Space Flying Vehicles for dirigible and flapping-wing aircraft, it is characterized in that, the flapping-wing aircraft that the dirigible (1) comprising top is connected with bottom.
2. a kind of Near Space Flying Vehicles with dirigible and flapping-wing aircraft according to claim 1, it is characterized in that, described dirigible (1) comprises hull (12), and is positioned at dirigible fin (9) and the dirigible horizontal stabilizer (10) of hull (12) afterbody.
3. a kind of Near Space Flying Vehicles with dirigible and flapping-wing aircraft according to claim 1, it is characterized in that, described flapping-wing aircraft comprises airframe, and is arranged at front wing (6) and the rear wing (7) of airframe.
4. a kind of Near Space Flying Vehicles with dirigible and flapping-wing aircraft according to claim 1, is characterized in that, dirigible (1) surface is provided with solar panel.
5. according to a kind of Near Space Flying Vehicles with dirigible and flapping-wing aircraft in claim 1-4 described in any one, it is characterized in that, flapping-wing aircraft wing is composite material, can adopt tapered airfoil, the straight wing, delta wing or bionical wing structure.
6. a kind of Near Space Flying Vehicles with dirigible and flapping-wing aircraft according to claim 5, it is characterized in that, also comprise a connecting device (11), described dirigible (1) is connected by described connecting device (11) with flapping-wing aircraft.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201520438305.0U CN204822081U (en) | 2015-06-24 | 2015-06-24 | Nearly spacecraft with dirigible and ornithopter |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201520438305.0U CN204822081U (en) | 2015-06-24 | 2015-06-24 | Nearly spacecraft with dirigible and ornithopter |
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| Publication Number | Publication Date |
|---|---|
| CN204822081U true CN204822081U (en) | 2015-12-02 |
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Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201520438305.0U Expired - Fee Related CN204822081U (en) | 2015-06-24 | 2015-06-24 | Nearly spacecraft with dirigible and ornithopter |
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| Country | Link |
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| CN (1) | CN204822081U (en) |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN106005351A (en) * | 2016-07-06 | 2016-10-12 | 深圳市迪西姆科技开发股份有限公司 | Flapping wing type bionic intelligent balloon and operation method thereof |
-
2015
- 2015-06-24 CN CN201520438305.0U patent/CN204822081U/en not_active Expired - Fee Related
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN106005351A (en) * | 2016-07-06 | 2016-10-12 | 深圳市迪西姆科技开发股份有限公司 | Flapping wing type bionic intelligent balloon and operation method thereof |
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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: 20151202 Termination date: 20160624 |
|
| CF01 | Termination of patent right due to non-payment of annual fee |