CN105597334B - A kind of solid-rocket toter for carrying telecontrolled aircraft - Google Patents
A kind of solid-rocket toter for carrying telecontrolled aircraft Download PDFInfo
- Publication number
- CN105597334B CN105597334B CN201510607381.4A CN201510607381A CN105597334B CN 105597334 B CN105597334 B CN 105597334B CN 201510607381 A CN201510607381 A CN 201510607381A CN 105597334 B CN105597334 B CN 105597334B
- Authority
- CN
- China
- Prior art keywords
- solid
- rocket
- regurgitate
- piston
- rocket body
- 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
Abstract
The present invention provides a kind of solid-rocket toter for carrying telecontrolled aircraft, and it includes：Rocket body, radome fairing, parachute, carrying compartment, regurgitate piston, Solid propeller, empennage and controller；Telecontrolled aircraft is carried to certain height by the present invention using the solid-rocket toter for carrying telecontrolled aircraft, and then telecontrolled aircraft is dished out from carrying compartment.Telecontrolled aircraft is started working after leaving carrying compartment, is saved from ground to the energy consumed in the air, extends its endurance, ground is returned under the power of itself after end-of-job；After solid carriers model completes carrying duty, ground is returned in the presence of parachute, and can be with Reusability.
Description
Technical field
The invention belongs to aerospace model technical field, and in particular to a kind of solid-rocket delivery dress for carrying telecontrolled aircraft
Put.
Background technology
Many telecontrolled aircrafts are all self-contained batteries as the energy at present, there is provided its power to fly, it is deep to be liked by model
Good person's likes.But due to the working time of battery electric energy that is shorter, and being consumed from ground into aerial flight course
It is larger, cause the endurance of telecontrolled aircraft relatively low.If telecontrolled aircraft can be made to take off in the air, it can be extended
The task such as working time, the Aerial photography carried out for application remoting aircraft is significant.
The content of the invention
In view of this, it is an object of the invention to provide a kind of solid-rocket toter for carrying telecontrolled aircraft, save
Telecontrolled aircraft extends its endurance of telecontrolled aircraft from ground to the energy consumed in the air.
The solid-rocket toter of the carrying telecontrolled aircraft of the present invention, it includes：Rocket body, radome fairing, parachute, fortune
Carry cabin, regurgitate piston, Solid propeller, empennage and controller；
Rocket body is cylindrical section, and bottom is provided with closed end cap, open top end；Carrying compartment includes：Round bottom plate, two and half
Cylindrical section and two and half dome plates, round bottom plate, two semicircular cylinder sections and two and half dome plates are spliced into a complete cylinder,
And the elastic threads that the position bonding spliced between two semicircular cylinder sections, between two and half dome plates is shunk, the position of other splicings
Put and be adhesively fixed；Telecontrolled aircraft is placed with carrying compartment；
Annexation is：
Empennage is installed on the bottom periphery face of rocket body, and radome fairing is socketed on the top of rocket body；In rocket body
Portion is sequentially provided with controller, Solid propeller from bottom to top, regurgitates piston, carrying compartment, parachute, and controller and solid
Propeller is both secured in rocket body, is regurgitated piston, carrying compartment and rocket body and is slidably matched；The end cap and solid propellant propulsion of rocket body
Between device, Solid propeller and regurgitate between piston, regurgitate and gap is left between piston and carrying compartment；Solid propeller with it is anti-
Between spray piston, regurgitate between piston and carrying compartment, between radome fairing and parachute, between parachute and rocket body by anti-
Rope of plaited plants connects.
Further, Solid propeller includes：Two plectanes and four solid engines, the home position pair of two plectanes
Title is provided with a central through hole, is arranged with three through holes at the central through hole periphery on two plectanes, two plectanes
A solid engines are provided between central through hole, three solid engines are provided between three pairs of through holes of two plectanes.
Further, the carrying step of described solid-rocket toter includes：
Step 1, after 4 solid engines for lighting Solid propeller, 4 solid engines produce thrust, drive solid
Rocket toter is flown in the air；
Step 2, after solid-rocket toter reaches specified altitude assignment, solid engines main thrust end-of-job is assert,
3 solid engines being symmetrically installed are stopped in controller control Solid propeller, and control the solid installed in center
Engine, which performs, regurgitates work, i.e., central solid engines to Solid propeller and regurgitate the space penetrating gas between piston
Body；
Step 3, regurgitate piston Solid propeller regurgitate gas effect under, regurgitate piston and its promotion carrying compartment,
Parachute slides inside rocket body to the direction of radome fairing together, until promote radome fairing depart from rocket body, then radome fairing,
Parachute, carrying compartment and regurgitate piston and depart from rocket body successively, the solid engines in now controller control center stop regurgitating
Work；
Step 4, after carrying compartment departs from rocket body, the axial limiting effect of rocket body, in the presence of elastic threads, two are lost
Separated between individual semicircular cylinder section, between two and half dome plates, telecontrolled aircraft departs from carrying compartment；
Step 5, after telecontrolled aircraft leaves carrying compartment, started working in the presence of itself electric energy；Solid-rocket delivery dress
Start to fall after putting flight to peak, now parachute is opened and started working, and in the presence of parachute, passes through fireproof rope
The rocket body of connection, radome fairing, carrying compartment and regurgitate piston and return to ground safely.
Further, empennage is four, and is symmetrically mounted on rocket body, and the fixed structure of empennage and Solid propeller
Unitary form is designed to, and is fixedly connected using splicing form with rocket body.
Further, one igniter head of installation inside the jet pipe of each solid engines, for starting solid engines.
The present invention has the advantages that：
Telecontrolled aircraft is carried to certain height using the solid-rocket toter for carrying telecontrolled aircraft, then will be distant
Control aircraft is dished out from carrying compartment.Telecontrolled aircraft is started working after leaving carrying compartment, is saved from ground to the energy consumed in the air
Amount, extends its endurance, ground is returned under the power of itself after end-of-job；Solid carriers model completes carrying duty
Afterwards, ground is returned in the presence of parachute, and can be with Reusability.
Brief description of the drawings
Fig. 1 is the solid-rocket toter structural representation of the carrying telecontrolled aircraft of the present invention.
Embodiment
The present invention will now be described in detail with reference to the accompanying drawings and examples.
As shown in figure 1, the solid-rocket toter of the carrying telecontrolled aircraft of the present invention, it includes：Rocket body 1, rectification
Cover 2, parachute 3, carrying compartment 4, regurgitate piston 5, Solid propeller 6, empennage 7 and controller；
The bottom of rocket body 1 is provided with closed end cap, open top end；Carrying compartment 4 includes：Round bottom plate, two semicircular cylinder sections
With two and half dome plates, round bottom plate, two semicircular cylinder sections and two and half dome plates are spliced into a complete cylinder, and two
The elastic threads that the position bonding spliced between individual semicircular cylinder section, between two and half dome plates is shunk, the position bonding of other splicings
It is fixed；Telecontrolled aircraft is placed with carrying compartment 4；
Empennage 7 is installed on the bottom periphery face of rocket body 1, and radome fairing 2 is socketed on the top of rocket body 1；In rocket body 1
Inside controller, Solid propeller 6 are sequentially provided with from bottom to top, regurgitates piston 5, carrying compartment 4, parachute 3, and control
Device and Solid propeller 6 are both secured in rocket body 1, are regurgitated piston 5, carrying compartment 4 and rocket body 1 and are slidably matched；Rocket body 1
Between end cap and Solid propeller 6, Solid propeller 6 and regurgitate between piston 5, regurgitate and left between piston 5 and carrying compartment 4
Gap；Solid propeller 6 and regurgitate between piston 5, regurgitate between piston 5 and carrying compartment 4, between radome fairing 2 and parachute 3,
Connected between parachute 3 and rocket body 1 by fireproof rope；For carrying compartment 4 at rocket 1 inside of body, rocket body 1 is to carrying compartment 4
Play axial limiting effect.
Solid propeller 6 includes：Two plectanes and four solid engines, the home position of two plectanes are arranged with one
Individual central through hole, is arranged with three through holes at the central through hole periphery on two plectanes, the central through holes of two plectanes it
Between be provided with a solid engines, be provided with three solid engines between three pairs of through holes of two plectanes.
The carrying step of the solid-rocket toter of described carrying telecontrolled aircraft includes：
Step 1, after 4 solid engines for lighting Solid propeller 6,4 solid engines produce thrust, drive solid
Rocket toter is flown in the air；
Step 2, after solid-rocket toter reaches specified altitude assignment, solid engines main thrust end-of-job is assert,
Controller controls 3 solid engines being symmetrically installed to be stopped, and it is anti-to control the solid engines installed in center to perform
Work is sprayed, i.e. central solid engines to Solid propeller 6 and regurgitate the space penetrating gas between piston 5；
Step 3, regurgitate piston 5 Solid propeller 6 regurgitate gas effect under, regurgitate piston 5 and its promote delivery
Cabin 4, parachute 3 slide inside rocket body 1 to the direction of radome fairing 2 together, until promoting radome fairing 2 to depart from rocket body 1, so
Radome fairing 2, parachute 3, carrying compartment 4 and regurgitate piston 5 afterwards and depart from rocket body 1 successively, the solid in now controller control center
Engine stop regurgitates work；
Step 4, after carrying compartment 4 departs from rocket body 1, the effect of contraction of rocket body 1, work of the carrying compartment 4 in elastic threads are lost
Under, separated between two semicircular cylinder sections, between two and half dome plates, telecontrolled aircraft departs from carrying compartment 4；
Step 5, after telecontrolled aircraft leaves carrying compartment 4, started working in the presence of itself electric energy；Solid-rocket delivery dress
Start to fall after putting flight to peak, now parachute 3 is opened and started working, and in the presence of parachute 3, passes through fire prevention
Restrict connection rocket body 1, radome fairing 2, carrying compartment 4 and regurgitate piston 5, safety return to ground.
Rocket body 1 is designed to conventional cylindrical section, and is process using compression molding technology.
The head design of radome fairing 2 has fixed skeleton structure into elliposoidal, the indoor design of radome fairing, and in skeleton knot
Counterweight lead is installed on structure.
Two semicircular cylinder sections of carrying compartment 4 are designed with skeleton structure.
Empennage 7 is four, and is symmetrically mounted on rocket body 1, and the fixed structure of empennage 7 and Solid propeller 6 designs
Integral form, it is connected using splicing form with rocket body 1.
One igniter head of installation, for starting solid engines, realizes that rocket pushes away inside the jet pipe of each solid engines
Enter the function of system 6.
In summary, presently preferred embodiments of the present invention is these are only, is not intended to limit the scope of the present invention.
Within the spirit and principles of the invention, any modification, equivalent substitution and improvements made etc., it should be included in the present invention's
Within protection domain.
Claims (3)
- A kind of 1. solid-rocket toter for carrying telecontrolled aircraft, it is characterised in that including：Rocket body (1), radome fairing (2), Parachute (3), carrying compartment (4), regurgitate piston (5), Solid propeller (6), empennage (7) and controller；Rocket body (1) is cylindrical section, and bottom is provided with closed end cap, open top end；Carrying compartment (4) includes：Round bottom plate, two Semicircular cylinder section and two and half dome plates, round bottom plate, two semicircular cylinder sections and two and half dome plates are spliced into a complete cylinder Body, and the elastic threads that the position bonding spliced between two semicircular cylinder sections, between two and half dome plates is shunk, other splicings Position is adhesively fixed；Telecontrolled aircraft is placed with carrying compartment (4)；Annexation is：Empennage (7) is installed on the bottom periphery face of rocket body (1), and radome fairing (2) is socketed on the top of rocket body (1)；In fire The inside of rocket body (1) be sequentially provided with from bottom to top controller, Solid propeller (6), regurgitate piston (5), carrying compartment (4), Parachute (3), and controller and Solid propeller (6) are both secured in rocket body (1), regurgitate piston (5), carrying compartment (4) with Rocket body (1) is slidably matched；Between the end cap and Solid propeller (6) of rocket body (1), Solid propeller (6) and regurgitate piston (5) between, regurgitate and leave gap between piston (5) and carrying compartment (4)；Solid propeller (6) and regurgitate between piston (5), Regurgitate between piston (5) and carrying compartment (4), between radome fairing (2) and parachute (3), between parachute (3) and rocket body (1) Connected by fireproof rope；Solid propeller (6) includes：Two plectanes and four solid engines, the home position of two plectanes are arranged with one Central through hole, is arranged with three through holes at the central through hole periphery on two plectanes, the central through holes of two plectanes it Between be provided with a solid engines, be provided with three solid engines between three pairs of through holes of two plectanes；The carrying step of described solid-rocket toter includes：Step 1, after 4 solid engines for lighting Solid propeller (6), 4 solid engines produce thrust, drive solid fire Arrow toter is flown in the air；Step 2, after solid-rocket toter reaches specified altitude assignment, solid engines main thrust end-of-job, control are assert 3 solid engines being symmetrically installed are stopped in device control Solid propeller (6), and control the solid hair installed in center Motivation, which performs, regurgitates work, i.e., central solid engines to Solid propeller (6) and regurgitate the space penetrating between piston (5) Gas；Step 3, regurgitate piston (5) Solid propeller (6) regurgitate gas effect under, regurgitate piston (5) and its promote fortune Carry cabin (4), parachute (3) to slide to the direction of radome fairing (2) in rocket body (1) inside together, until promoting radome fairing (2) de- From rocket body (1), then radome fairing (2), parachute (3), carrying compartment (4) and regurgitate piston (5) and depart from rocket body (1) successively, The solid engines in now controller control center stop regurgitating work；Step 4, after carrying compartment (4) departs from rocket body (1), the axial limiting effect of rocket body (1) is lost, in the effect of elastic threads Under, separated between two semicircular cylinder sections, between two and half dome plates, telecontrolled aircraft departs from carrying compartment (4)；Step 5, after telecontrolled aircraft leaves carrying compartment (4), started working in the presence of itself electric energy；Solid-rocket toter Start to fall after flight to peak, now parachute (3) is opened and started working, in the presence of parachute (3), by anti- The rocket body (1) of rope of plaited plants connection, radome fairing (2), carrying compartment (4) and regurgitate that piston (5) is safe to return to ground.
- 2. the solid-rocket toter of telecontrolled aircraft is carried as claimed in claim 1, it is characterised in that empennage (7) is four It is individual, and be symmetrically mounted on rocket body (1), and the fixed structure of empennage (7) and Solid propeller (6) is designed to unitary form, And it is fixedly connected using splicing form with rocket body (1).
- 3. the solid-rocket toter of telecontrolled aircraft is carried as claimed in claim 1, it is characterised in that each solid starts One igniter head of installation inside the jet pipe of machine, for starting solid engines.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201510607381.4A CN105597334B (en) | 2015-09-22 | 2015-09-22 | A kind of solid-rocket toter for carrying telecontrolled aircraft |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201510607381.4A CN105597334B (en) | 2015-09-22 | 2015-09-22 | A kind of solid-rocket toter for carrying telecontrolled aircraft |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN105597334A CN105597334A (en) | 2016-05-25 |
| CN105597334B true CN105597334B (en) | 2017-11-21 |
Family
ID=55978018
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201510607381.4A Active CN105597334B (en) | 2015-09-22 | 2015-09-22 | A kind of solid-rocket toter for carrying telecontrolled aircraft |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN105597334B (en) |
Families Citing this family (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| IL262690B2 (en) | 2018-08-19 | 2023-03-01 | Israel Aerospace Ind Ltd | Launch system |
| CN110282161A (en) * | 2019-05-27 | 2019-09-27 | 上海机电工程研究所 | Radome fairing separator and its separation method |
| CN113101679B (en) * | 2021-04-17 | 2022-08-09 | 西北工业大学 | Three-load separating device of model rocket |
| CN113362692A (en) * | 2021-06-16 | 2021-09-07 | 中国人民解放军国防科技大学 | Teaching aid based on water rocket boosting glider |
| CN114987771B (en) * | 2022-08-05 | 2022-11-01 | 西安羚控电子科技有限公司 | Unmanned aerial vehicle and carrier buffering separator |
Family Cites Families (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US3664056A (en) * | 1970-08-07 | 1972-05-23 | Victor Stanzel | Jet propelled model vehicle |
| US4901949A (en) * | 1988-03-11 | 1990-02-20 | Orbital Sciences Corporation Ii | Rocket-powered, air-deployed, lift-assisted booster vehicle for orbital, supraorbital and suborbital flight |
| CN2048381U (en) * | 1989-02-23 | 1989-11-29 | 黄玮 | Toy spacecraft |
| CN2169462Y (en) * | 1993-07-10 | 1994-06-22 | 航空航天工业部第四研究院第四十一研究所 | Model rocket |
| US6286410B1 (en) * | 1999-05-10 | 2001-09-11 | The United States Of Americas As Represented By The Secretary Of The Navy | Buoyantly propelled submerged canister for air vehicle launch |
| CN201081629Y (en) * | 2007-07-22 | 2008-07-02 | 中国航天科技集团公司第五研究院第五一八研究所 | Large-size rocket mockup |
-
2015
- 2015-09-22 CN CN201510607381.4A patent/CN105597334B/en active Active
Also Published As
| Publication number | Publication date |
|---|---|
| CN105597334A (en) | 2016-05-25 |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| CN105597334B (en) | A kind of solid-rocket toter for carrying telecontrolled aircraft | |
| CN104843181B (en) | A kind of oil electric mixed dynamic fixed-wing VUAV system | |
| US20080184906A1 (en) | Long range hybrid electric airplane | |
| CN109279005A (en) | The aircraft of vertical takeoff and landing | |
| EP2962885A1 (en) | Hybrid power system for piston engine aircrafts | |
| RU2016130683A (en) | HYBRID ELECTRIC POWER TRANSMISSION FOR UNMANNED AERIAL VEHICLES AND LANDING | |
| US20160176533A1 (en) | Removable auxiliary power device for aircraft and aircraft adapted to use at least one such device | |
| RU109740U1 (en) | HELICOPTER RESCUE DEVICE | |
| CN104326086B (en) | The quick parachute opener of parachute | |
| CN106005414B (en) | A kind of relief goods vehicle based on Canon launching | |
| CN202295289U (en) | Special high-speed unmanned aerial vehicle | |
| RU2682157C1 (en) | Aircraft with additional removable wing | |
| CN106762157B (en) | Big aircraft floor starting device | |
| CN102180269A (en) | Multifunctional helicopter | |
| WO2019145694A1 (en) | A vertical take off and landing flying machine | |
| CN207748028U (en) | A kind of Automatic-falling unmanned plane protective device | |
| CN206394895U (en) | Oil electric mixed dynamic rotor manned aircraft | |
| Saeed et al. | A feasibility assessment of annular winged VTOL flight vehicles | |
| CN205738062U (en) | A kind of unmanned plane propeller | |
| RU2353546C2 (en) | Mobile aircraft rocket-and-space system | |
| RU2013139791A (en) | MISCELLANEOUS AIRPLANE FOR PASSENGERS AND LOADS WITH ELECTRIC MOTOR | |
| RU2571153C1 (en) | Manned vtol aircraft with extra hydrogen module | |
| KR20190045789A (en) | A Vertical take-off and landing aircraft | |
| CN205273874U (en) | Solar aircraft | |
| CN203767066U (en) | Unmanned aerial vehicle with grounded buffering fairing |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| C06 | Publication | ||
| PB01 | Publication | ||
| C10 | Entry into substantive examination | ||
| SE01 | Entry into force of request for substantive examination | ||
| GR01 | Patent grant | ||
| GR01 | Patent grant |