CN209506094U - Near space vehicle jettison system - Google Patents
Near space vehicle jettison system Download PDFInfo
- Publication number
- CN209506094U CN209506094U CN201822045689.6U CN201822045689U CN209506094U CN 209506094 U CN209506094 U CN 209506094U CN 201822045689 U CN201822045689 U CN 201822045689U CN 209506094 U CN209506094 U CN 209506094U
- Authority
- CN
- China
- Prior art keywords
- near space
- space vehicle
- frame
- utility
- hanging ring
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Active
Links
Landscapes
- Emergency Lowering Means (AREA)
Abstract
The utility model provides a kind of near space vehicle jettison system, and near space vehicle jettison system includes: near space vehicle, launches frame, carry rigging and cutter；Its tail portion of near space vehicle is provided with hanging ring；It launches and is provided with hanging ring on frame；Carry rigging is separately connected the hanging ring being arranged on the hanging ring and near space vehicle launched and be arranged on frame；Cutter is arranged on carry rigging.The utility model uses constraint component of the tail portion hanging ring of small in volume as near space vehicle before dispensing, does not need installation other structures part, significantly reduces the influence launched to aircraft flight performance.
Description
Technical field
The utility model relates to aircraft field more particularly to a kind of near space vehicle jettison systems.
Background technique
Near space is the airspace on 20~100 kilometers of span ground, due to its important development and application values in the world
On attract extensive attention.Near space vehicle, which refers to, makees long-term, follow-on mission aircraft near space or sub- track flies
Row device or hypersonic cruise air vehicle in close to space vehicle, such aircraft is in communication support, information acquisition, electronics pressure
System, early warning, civilian etc. are with development potential.
Two hang-ups are mainly faced by the aircraft of autonomous flight near space height at present: being to need the ascent stage first
Unstable flow area is passed through, housing construction destruction is easily led to；The propeller power needed for section that followed by climbs is big, leads to energy source and power system
System and construction weight dramatically increase, and then payload capability is caused to significantly reduce.Facing air-drop discharge technique can be good at solving
Above-mentioned two problems can not only make the design of unmanned plane more targeted, improve the efficiency of design point, and can also reduce pair
Ground landing condition, mating guarantee requirement, the design of near space vehicle system is greatly reduced, using difficulty.
Implementing to face in sky launch process, carried out after aircraft is brought near space height using aerostatics platform controlled
It launches, is a kind of more feasible scheme.In order to improve the service efficiency of system, no less than three are carried out usually in flight
Business is let alone in the air-drop of facing of frame aircraft, and multi rack time is defined as no less than three frame aircraft herein.
Currently, implementing to face the precedent that air-drop is put there are no multi rack time near space vehicle in the world, in the utility model
Near space jettison system solution will be provided thus.
Utility model content
(1) technical problems to be solved
The utility model provides a kind of near space vehicle jettison system, set forth above at least partly to solve
Technical problem.
(2) technical solution
One aspect according to the present utility model provides a kind of near space vehicle jettison system, comprising: close on sky
Between aircraft, the tail portion of housing construction is provided with hanging ring；Frame is launched, is provided with hanging ring on the dispensing frame；Carry rigging, point
The hanging ring being arranged on the hanging ring and the near space vehicle being arranged on the dispensing frame is not connected；Cutter is arranged in institute
It states on carry rigging.
In some embodiments of the utility model, the dispensing frame includes n partition cabin, wherein n >=1；
In some embodiments of the utility model, the hanging ring being arranged on frame of launching is located at each partition cabin
Top center.
In some embodiments of the utility model, further includes: shock insulation baffle is mounted in the dispensing frame, and is wrapped up
On the dispensing frame；The shock insulation baffle is foamed material.
In some embodiments of the utility model, further includes: bottom bracket is mounted on each partition on the dispensing frame
The bottom in cabin.
In some embodiments of the utility model, the dispensing frame is truss frame structure.
In some embodiments of the utility model, the cutter is priming system cutter.
(3) beneficial effect
It can be seen from the above technical proposal that the utility model near space vehicle jettison system at least has and following has
One of beneficial effect or in which a part:
(1) the utility model uses pact of the tail portion hanging ring of small in volume as near space vehicle before dispensing
Beam component does not need installation other structures part, significantly reduces the influence launched to aircraft flight performance.
(2) the utility model uses constraint of the flexible rigging as near space vehicle before dispensing, gives aircraft
Certain freedom degree prevents it from occurring structure destruction in uphill process.
(3) the utility model respectively constrains multi rack time near space vehicle using the truss frame of subdivision room,
It prevents from influencing each other between different aircraft, structure is practical, simple and reliable.
(4) the utility model is cut off flexible constraint rigging using priming system cutter, completes near space vehicle
Dispensing task, system is safe and reliable, improves the probability of Mission Success.
(5) the utility model uses near space floating platform as female platform, carries multi rack time near space aerostatics
Dispensing task is executed, system service efficiency is improved, reduces research cost.
Detailed description of the invention
Fig. 1 is the structural schematic diagram of the utility model embodiment near space vehicle jettison system.
Fig. 2 is the structural representation of near space vehicle in the utility model embodiment near space vehicle jettison system
Figure.
Fig. 3 is the structural schematic diagram that frame is launched in the utility model embodiment near space vehicle jettison system.
Fig. 4 is the structural schematic diagram of shock insulation baffle in the utility model embodiment near space vehicle jettison system.
[the utility model embodiment main element symbol description in attached drawing]
1: near space vehicle；
1-1: housing construction；
1-2: hanging ring；
2- launches frame；
2-1: truss frame；
2-2: hanging ring；
3: shock insulation baffle；
4: bottom bracket；
5: carry rigging；
6: cutter.
Specific embodiment
The utility model provides a kind of near space vehicle jettison system, near space vehicle jettison system packet
Include: near space vehicle launches frame, carry rigging and cutter；Its tail portion of near space vehicle is provided with hanging ring；It launches
Hanging ring is provided on frame；Carry rigging, which is separately connected, launches hanging of being arranged on the hanging ring and near space vehicle that are arranged on frame
Ring；Cutter is arranged on carry rigging.The utility model uses the tail portion hanging ring of small in volume to fly as near space
Constraint component of the row device before dispensing does not need installation other structures part, significantly reduces dispensing to aircraft flight performance
Influence.
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 some embodiments will be done referring to appended attached drawing in rear and more comprehensively describe to property, some of but simultaneously
Not all embodiment will be shown.In fact, the various embodiments of the utility model can be realized in many different forms, without
It should be construed as limited to this several illustrated embodiment；Relatively, it theses embodiments are provided so that the utility model meets to be applicable in
Legal requirement.
In first exemplary embodiment of the utility model, a kind of near space vehicle jettison system is provided.
Fig. 1 is the structural schematic diagram of the utility model embodiment near space vehicle jettison system.Fig. 2 is the utility model embodiment
The structural schematic diagram of near space vehicle near space vehicle jettison system.Fig. 3 closes on for the utility model embodiment
The structural schematic diagram of frame is launched in spacecraft jettison system.Fig. 4 is the throwing of the utility model embodiment near space vehicle
The structural schematic diagram of shock insulation baffle in place system.As shown in Figure 1, the utility model near space vehicle jettison system includes:
Near space vehicle 1 launches frame 2, carry rigging 5 and cutter 6.The hanging ring 1-2 and dispensing frame 2 of near space vehicle 1
Hanging ring 2-2 by carry rigging 5 connect, cutter 6 be arranged on carry rigging 5, for cutting carry rigging 5, make to close on
Spacecraft 1 is separated with frame 2 is launched, and carries out the dispensing of near space vehicle 1.The utility model smart structural design, no
It needs to install other structures part, significantly reduces the influence launched to aircraft flight performance.
Each component part is described in detail below, in which:
Near space vehicle 1, as shown in Fig. 2, including housing construction 1-1 and hanging for the tail portion housing construction 1-1 is arranged in
Ring 1-2.
Frame 2 is launched, as shown in figure 3, being made of truss frame 2-1, as the primary load bearing component for launching frame 2.It is general to use
45 steel tubings are process.Further, launching frame 2 includes multiple partition cabins, provides a kind of tool in one embodiment
There are three the dispensing framves 2 in partition cabin.Further, launching the hanging ring 2-2 on frame 2 can be set in each partition cabin
Top center.
Carry rigging 5, the freedom degree of near space vehicle 1, carry rigging 5 pass through before launching as flexible connection constraint
After hanging ring 1-2 near space vehicle 1, it is fixed on the hanging ring 2-2 for launching frame 2 using knot form.Carry rigging 5 is logical
Frequently with the super-macromolecule polyethylene rope with high intensity.
Cutter 6 can select priming system cutter.
Selectable includes: shock insulation baffle 3, is mounted in the dispensing frame 2, and is wrapped on the dispensing frame 2.One
In specific embodiment, shock insulation baffle 3 is separately mounted to inside the corresponding truss frame 2-1 in three partition cabins for launching frame 2,
It is wrapped in the surrounding for launching the truss frame 2-1 of frame 2, prevent the near space vehicle 1 in uphill process and launches the generation of frame 2
The structure safety of near space vehicle 1 is protected in collision.Specifically, the shock insulation baffle 3 of each partition cabin interior is according to difference
1 shape of near space vehicle and it is different.General shock insulation baffle 3 selects foamed material.
Further selectable includes: bottom bracket 4, is mounted on the bottom in each partition cabin, uses binding strap and purlin
The 2-1 connection of frame frame prevents shock insulation baffle 3 mobile.
In first exemplary embodiment of the utility model, a kind of near space vehicle jettison system is additionally provided
Application method, three near space vehicles can be launched, be specifically included:
Step S100: after three near space vehicles are debugged, near space vehicle is adjusted to vertical side
To, and the hanging ring of near space vehicle tail portion direction is launched into top of the trellis.
Step S200: carry rigging connects near space vehicle one and separates the hanging ring in cabin and launch the hanging ring of frame, and
Carry rigging both ends are separated into knotting on compartment roof hanging ring in dispensing frame one, it is ensured that stable connection.In other partition cabins
In repeat the above steps.Cutter is installed on carry rigging respectively again, selects priming system cutter here.
Also selectable includes: to be packed into three shock insulation baffles to launch in the corresponding truss frame in frame partition cabin.In turn
It reuses binding strap and bottom bracket is fixed on dispensing frame bottom, to prevent the movement of shock insulation baffle.
Step S300: floating platform is discharged by ground infrastructure, and floating platform is made to carry close to space vehicle
The lift-off of device jettison system.Floating platform selects aerostat in the present embodiment, passes through ground after helium is filled with inside aerostat
Face infrastructure is discharged.
Step S400: after reaching predetermined release altitude and launching region, successively priming system cutter is powered on, respectively by three
Frame near space vehicle is launched.
So far, attached drawing is had been combined the utility model embodiment is described in detail.It should be noted that in attached drawing
Or in specification text, the implementation for not being painted or describing is shape known to a person of ordinary skill in the art in technical field
Formula is not described in detail.In addition, the above-mentioned definition to each element and method be not limited in mentioning in embodiment it is various
Specific structure, shape or mode, those of ordinary skill in the art simply can be changed or be replaced to it.
According to above description, those skilled in the art should have the utility model near space vehicle jettison system
Clearly understanding.
In conclusion the utility model uses near space floating platform as female platform, multi rack time can be carried and closed on
Space aerostatics executes dispensing task, improves system service efficiency, reduces research cost.
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.
It unless there are known entitled phase otherwise anticipates, the numerical parameter in this specification and appended claims is approximation, energy
The resulting required characteristic changing of content that enough bases pass through the utility model.Specifically, all be used in specification and right
The number of content, reaction condition of composition etc. is indicated in it is required that, it is thus understood that be the term by " about " in all situations
It is modified.Under normal circumstances, express meaning refer to comprising by specific quantity ± 10% variation in some embodiments,
± 5% variation in some embodiments, ± 1% variation in some embodiments, in some embodiments ± 0.5% change
Change.
Furthermore word "comprising" does not exclude the presence of element or step not listed in the claims.It is located in front of the element
Word "a" or "an" does not exclude the presence of multiple such elements.
In addition, unless specifically described or the step of must sequentially occur, there is no restriction in the above institute for the sequence of above-mentioned steps
Column, and can change or rearrange according to required design.And above-described embodiment can be based on the considerations of design and reliability, that
This mix and match is used using or with other embodiments mix and match, i.e., the technical characteristic in different embodiments can be freely combined
Form more embodiments.
Similarly, it should be understood that in order to simplify the utility model and help to understand one in each utility model aspect
Or it is multiple, in the description above to the exemplary embodiment of the utility model, each feature of the utility model is sometimes by one
It rises and is grouped into single embodiment, figure or descriptions thereof.However, the method for the utility model should not be construed to instead
Reflect following intention: the requires of the utility model i.e. claimed is more than feature expressly recited in each claim
Feature.More precisely, as reflected in the following claims, being in terms of utility model practical less than front
All features of novel single embodiment.Therefore, it then follows thus claims of specific embodiment are expressly incorporated in this
Specific embodiment, wherein 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 (7)
1. a kind of near space vehicle jettison system characterized by comprising
The tail portion of near space vehicle, housing construction is provided with hanging ring；
Frame is launched, is provided with hanging ring on the dispensing frame；
Carry rigging is separately connected the hanging ring being arranged on the hanging ring and the near space vehicle being arranged on the dispensing frame；
Cutter is arranged on the carry rigging.
2. near space vehicle jettison system according to claim 1, which is characterized in that the dispensing frame includes n
Separate cabin, wherein n >=1.
3. near space vehicle jettison system according to claim 2, which is characterized in that be arranged on the dispensing frame
Hanging ring is located at the top center in each partition cabin.
4. near space vehicle jettison system according to claim 1, which is characterized in that further include:
Shock insulation baffle is mounted in the dispensing frame, and is wrapped on the dispensing frame；The shock insulation baffle is foamed material.
5. near space vehicle jettison system according to claim 2, which is characterized in that further include:
Bottom bracket is mounted on the bottom in each partition cabin on the dispensing frame.
6. near space vehicle jettison system according to claim 1, which is characterized in that the dispensing frame is truss frame
Frame structure.
7. near space vehicle jettison system according to claim 1, which is characterized in that the cutter is priming system
Cutter.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201822045689.6U CN209506094U (en) | 2018-12-06 | 2018-12-06 | Near space vehicle jettison system |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201822045689.6U CN209506094U (en) | 2018-12-06 | 2018-12-06 | Near space vehicle jettison system |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN209506094U true CN209506094U (en) | 2019-10-18 |
Family
ID=68194481
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201822045689.6U Active CN209506094U (en) | 2018-12-06 | 2018-12-06 | Near space vehicle jettison system |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN209506094U (en) |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN109455300A (en) * | 2018-12-06 | 2019-03-12 | 中国科学院光电研究院 | Near space vehicle jettison system and its application method |
-
2018
- 2018-12-06 CN CN201822045689.6U patent/CN209506094U/en active Active
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN109455300A (en) * | 2018-12-06 | 2019-03-12 | 中国科学院光电研究院 | Near space vehicle jettison system and its application method |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| EP2046644B1 (en) | An unmanned aerial vehicle launching and landing system | |
| US11560229B2 (en) | High-efficiency method using unmanned aerial vehicles for firefighting | |
| EP1600370A2 (en) | High-aspect ratio hybrid airship | |
| US20050258306A1 (en) | Delta-winged hybrid airship | |
| CN204822083U (en) | For military use alert unmanned aerial vehicle system that uses of multipurpose | |
| US6220543B1 (en) | Safe and secure commercial air transportation | |
| GB2504132A (en) | A solar powered UAV launched from a high altitude balloon | |
| CN101301931A (en) | Method and apparatus for manufacturing compound vortex and compound vortex aerocraft | |
| CN1628053A (en) | System and method for enhancing the payload capacity, carriage efficiency, and adaptive flexibility of external stores mounted on an aerial vehicle | |
| CN109229409A (en) | A kind of aerial rapid fire system of cluster type small drone | |
| CN102910288A (en) | Multifunctional unmanned aerial vehicle provided with flexible stamping parafoil | |
| CN209506094U (en) | Near space vehicle jettison system | |
| CN110553550A (en) | anti-unmanned aerial vehicle net catches device in air | |
| CN109455300A (en) | Near space vehicle jettison system and its application method | |
| US9950781B2 (en) | Effector with ejectable stealth shell | |
| CN214729761U (en) | Unmanned aerial vehicle forces descending damper | |
| CN113232854A (en) | Distributed unmanned aerial vehicle platform applicable to ballistic launching and launching method | |
| CN202754145U (en) | Unmanned aerial vehicle with effective load fuselage | |
| CN111589016A (en) | High-altitude aviation fire extinguishing and disaster relief system | |
| Prior et al. | The future of battlefield micro air vehicle systems | |
| RU2353546C2 (en) | Mobile aircraft rocket-and-space system | |
| Tsach et al. | UAV systems development in IAI-Past, present & future | |
| CN114426096A (en) | Medium-short distance quick response support system | |
| CN215554116U (en) | Vertical take-off and landing unmanned aerial vehicle | |
| CN112141319B (en) | M-shaped variable sweepback folding unmanned aerial vehicle |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| GR01 | Patent grant | ||
| GR01 | Patent grant |