CN205819572U

CN205819572U - Unrestricted and without supporting leg the reusable sky of length penetrates carrier rocket

Info

Publication number: CN205819572U
Application number: CN201620568655.3U
Authority: CN
Inventors: 李鹏
Original assignee: Individual
Current assignee: Individual
Priority date: 2016-06-14
Filing date: 2016-06-14
Publication date: 2016-12-21
Anticipated expiration: 2026-06-14

Abstract

The utility model discloses unrestricted and without supporting leg the reusable sky of a kind of length and penetrate carrier rocket.Rocket body has relative strip opening up and down in carrier aircraft nose-gear position.During sliding race, the upper and lower cover plates of opening is unfolded into vertical passageway in rocket body, and nose-gear can normally put down.Form cavity in upper and lower cover plates closes at rocket body after taking off, filled up from the liquid in liquid case in carrier aircraft subsequently.Multiplexing configuration is similar to Roton carrier rocket, and rocket nose section has extensible rotor, and afterbody uses plug nozzle, must match with the stewart tabletop of platform placed at drop point in plug nozzle bottom surface.The surrounding of stewart platform must have and the equipment contacting and buttressing rocket body in the middle part of rocket body, in order to avoid rocket body is toppled over.Then rocket body can be the longest and without supporting leg.Load adapter afterbody must be jagged so that compatible with rotor system.

Description

Unrestricted and without supporting leg the reusable sky of length penetrates carrier rocket

Technical field

This utility model relates to a kind of carry air-launched on supersonic fighterplane or bomber fuselage center line hanger Reusable carrier rocket, particularly relating to a kind of rocket body head can be in front of before carrier aircraft nose-gear, without supporting leg Reusable sky penetrates carrier rocket.

Background technology

Utilize active service or retired supersonic fighterplane or bomber, sent out in the air by carry on its fuselage center line hanger The carrier rocket penetrated and the satellite delivery system realized, it is not necessary to develop carrier aircraft separately, have the advantages that to realize low cost.And delivery Being high-altitude supersonic speed during Separation, performance is higher.But existing carry is hung at supersonic fighterplane or bomber fuselage center line Air-launched carrier rocket on frame, its rocket body head must rise before otherwise making carrier aircraft after carrier aircraft nose-gear The frame that falls cannot put down, and causes the carrier aircraft cannot normally rolling start.It is shorter that sky so penetrates carrier rocket certainty length, fuel loading Amount is few, and carrying capacity is low.Without the reusable carrier rocket of the existing Roton configuration of corresponding patent, use up-thin-low-thick oval Platform shape rocket body, due to the widest bottom its rocket body, the supporting leg launched during its landing can be the smallest and the most exquisite.But this long truncated conical shape shows So it is not used to sky and penetrates carrier rocket.Change cylindrical rocket body into, then stand firm time in order to land, it is necessary to ensure that the supporting leg after expansion has Bigger width, can only use the biggest the longest supporting leg.But such supporting leg weight resistance is the biggest.Refer to load hereinafter Satellite or satellite/Upper Stage assembly.It addition, Roton rocket is Single Stage To Orbit, load can be placed on rocket body rear portion, after entering the orbit It is deployed in track by large-sized hatch door.And this sky to penetrate rocket be cylindrical rocket body, rearward diameter is extremely limited, and weight/HP ratio is straight Footpath is the most how many, it is impossible to open large-sized hatch door, so load must necessarily be placed in rocket front end.This just faces a load adaptation The problem that device afterbody interferes with rotor pivot.

Summary of the invention

First rocket body that technical problem is how to make a length overlength to be solved in the utility model not with carrier aircraft before The folding and unfolding of undercarriage is disturbed.For solving above-mentioned technical problem, the rocket body described by this utility model has opposing upper and lower two Individual strip opening, aperture position is just in the underface of the carrier aircraft nose-gear packed up.The cover plate of upper shed is downwards to rocket body Inside open；The cover plate of under shed is upwards opened in rocket body.The carrier aircraft hanging with rocket body is being parked in ground and is normally taking off During sliding race, upper and lower cover plates is all opened, and such nose-gear just can normally put down, and is vertically led to by what upper and lower opening was formed Road supports on the ground.When, after carrier aircraft rolling start, after carrier aircraft nose-gear is packed up, upper cover plate upwards closes, and lower cover is downward Guan Bi, makes rocket body outer surface be formed streamlined, and forms cavity in rocket body.Then, the liquid case in carrier aircraft fuselage passes through hanger On the cavity that formed in rocket body of pipeline add fuel or oxidant or simple substance propellant.Subsequently, full rocket body is launched to be held Row carrying duty.Sky described in the utility model penetrates carrier rocket can be the longest, sufficiently bulky, and carrying capacity is the biggest.Large volume Sky penetrate carrier rocket can have ready conditions employing the higher liquid launch vehicle of engine/motor specific impulse.

Second to be solved in the utility model technical problem is how thoroughly to remove supporting leg.Because of without supporting leg, so starting The bottom of machine must directly land, cannot the bell nozzle of stress so can not use, it is necessary to use plug nozzle.For guaranteeing plug Formula jet pipe is not damaged when landing, it is necessary to place a stewart platform at drop point, in order to equally substituting supporting leg provides Cushioning effect.The shape of plug nozzle bottom surface must match with stewart tabletop of platform.If plug nozzle bottom surface is convex ball During face, stewart tabletop of platform is necessary for concave spherical surface, or is all plane.When the rocket returned from high-altitude is under the effect of rotor Of short duration when substantially stopping to be suspended in above stewart platform, stewart platform is under the control of internal six degree of freedom software, and alignment is also Contact plug spout base face, completes to bear the task of its weight.Meanwhile, the surrounding of stewart platform must have and rocket body Middle part contacts and buttresses the equipment of rocket body, in order to avoid rocket body is toppled over.The equipment done so can be played the most, all at common knowledge model Among farmland, so being not belonging to the content of this utility model application.4 moving machine mechanical arm of the centripetal arrangement of such as circumference, etc..

3rd afterbody that technical problem is how to make load adapter to be solved in the utility model not with rotor pivot Disturb.Rotor pivot is positioned at rocket body axis, extends radially out 2 or 4 or 6 brachyplast arms to the rocket body of circumferential from oar pivot and cuts Face edge, then at end by hinged 2 or 4 or 6 rotors of flapping hinge.So the afterbody of truncated cone-shaped load adapter must have The concavity breach of battlement shape, breach number is equal to rotor number.So brachyplast arm just can reach circumferential edges through concavity breach.When After load separates with load adapter, load adapter also to separate immediately with rocket body, and then rotor is just freely rotatable.

Accompanying drawing explanation

With detailed description of the invention, this utility model is described in further detail below in conjunction with the accompanying drawings.Because of rocket nose section Rotor is not the claimed content of this utility model and in order to avoid unnecessary blocks and keep succinct, and Fig. 1-5 is not drawn into Rotor.

Fig. 1 to Fig. 5 is that the sky that this utility model length is not limited by carrier aircraft nose-gear penetrates one of carrier rocket specifically One group of schematic diagram of embodiment.

Fig. 6 is that the sky that this utility model length is not limited by carrier aircraft nose-gear is penetrated another of carrier rocket and is embodied as One schematic diagram of mode.

After Fig. 7 is trousers and load has disengaged from, load adapter also without departing from time, the rocket signal of band two panels rotor Figure.

Detailed description of the invention

Fig. 1, Fig. 2 and Fig. 5 are carrier aircraft and the rocket body state when ground static or rolling start.Fig. 2 is carrier aircraft and rocket body Side view when ground static or sliding race, Fig. 1 is the sectional view of line A-A along Fig. 2.In fig. 1 and 23 and 2 be respectively to The upper and lower cover plates opened in rocket body, 4 for carrier aircraft nose-gear (therefore parts are not belonging to this utility model, thus the purest schematically Draw), 1 and 5 is wallboard before and after rocket body storage tank, and 6 is liquid-transport pipe-line, and 7 is carrier aircraft center hanger, and 8 is hydraulically full carrier aircraft Internal storage tank, 11 is liquid-transport pipe-line outlet on rocket body storage tank squab panel.9 is the soft tank diaphragm gluedd joint with upper and lower cover plates, 10 is the another part diaphragm of soft tank, and such design makes the soft tank Automatic-expanding when upper and lower cover plates closes.Fig. 5 is Kinematic sketch of mechanism, 3 and 2 open inside rocket body respectively upper and lower cover plates.Fig. 3 and Fig. 4 is carrier aircraft and rocket body aloft flies State during row.Fig. 4 is side view when carrier aircraft and rocket body flight aloft, and Fig. 3 is the sectional view of line A-A along Fig. 4.At figure In 3 and Fig. 4,3 and 2 are respectively the upper and lower cover plates of Guan Bi, and 11 is liquid-transport pipe-line outlet on rocket body storage tank squab panel, and 8 is empty The internal storage tank of carrier aircraft, 12 is full rocket body storage tank.

It is that of the present utility model another has that the sky that length shown in Fig. 6 is not limited by carrier aircraft nose-gear penetrates carrier rocket Body embodiment.Fig. 6 depict by the mode that contrasts up and down the local-rocket body storage tank of rocket body ground static or sliding run and The two states of airflight.Soft tank not glue unlike unique from former embodiment is connected in upper and lower cover plates, soft Fuel tank is the column soft tank of an independent axial stretching.The first half correspondence carrier aircraft of Fig. 6 and rocket body are in ground static or sliding race State when taking off, 3 is the upper cover plate inwardly opened, and 13 is the column soft tank being axially in contraction state, column soft tank The ring-shaped edge of bottom is to be glued on the squab panel of rocket body storage tank, and the sidewall of column soft tank is place when without internal pressure In corrugation contraction state.State when the lower half correspondence carrier aircraft of Fig. 6 and rocket body flight aloft, 2 is under downward Guan Bi Cover plate, 14 is the column soft tank being axially in extended configuration.The liquid that the soft tank of compressive state can be poured into backs down.

Certainly, the sky that this length is not limited by carrier aircraft nose-gear penetrates carrier rocket also can use other structure, the completeest The full soft tank cancelling liner, is completely dependent on the sealing strip at upper and lower cover plates edge, to realize the sealing of storage tank.Such change is also Fall within protection domain of the present utility model.

Claims

1. unrestricted and without supporting leg the reusable sky of length penetrates carrier rocket, its multiplexing configuration as Roton carrier rocket, Rocket nose section has extensible rotor, it is characterised in that: first, the rocket body described by this utility model has two opposing upper and lower Strip opening, its position is just in the underface of the carrier aircraft nose-gear packed up, and the cover plate (3) of upper shed is downwards in rocket body Opening, the cover plate (2) of under shed is upwards opened in rocket body, and the carrier aircraft hanging with rocket body is being parked in ground and is normally taking off During sliding race, upper and lower cover plates is all opened, and such nose-gear just can normally put down, and is vertically led to by what upper and lower opening was formed Road supports on the ground, when, after carrier aircraft rolling start, after carrier aircraft nose-gear is packed up, upper cover plate upwards closes, and lower cover is downward Guan Bi, makes rocket body outer surface be formed streamlined, and with rocket body storage tank before and after wall (1,5) in rocket body, forms cavity, then, load Liquid case (8) in machine fuselage is by the pipeline (6) on hanger (7), through the outlet (11) on rocket body storage tank squab panel to rocket body The cavity of interior formation adds fuel or oxidant or simple substance propellant, and the fullest rocket body is launched execution carrying duty；Secondly, Reusable rocket body described by this utility model does not has supporting leg, and its afterbody must use plug nozzle (17), and at drop point Stewart platform is placed at place, and bottom surface and the stewart tabletop of platform of plug nozzle must match, after being convex spherical such as the former Person is concave spherical surface, or is all plane；3rd, the afterbody of load adapter (15) must have the concavity breach (16) of battlement shape, lacks Mouthful number equal to rotor blade (20) number, each breach must be able to allow radially-protruding, connect the short of oar pivot and flapping hinge (19) Branch arm (18) passes through, and after load separates with load adapter, load adapter and rocket body to be also subsequently isolated.

Unrestricted and without supporting leg the reusable sky of length the most according to claim 1 penetrates carrier rocket, wherein, in need to having The soft tank of lining, to realize the sealing of storage tank, the sidewall limit diaphragm (9) of the soft tank of liner and upper and lower cover plates are away from the side of rotating shaft Limit is gluedd joint, and the sidewall limit diaphragm (10) of the opposite side of soft tank glueds joint near the side of rotating shaft with upper and lower cover plates, works as upper and lower cover plates During Guan Bi, the soft tank of liner is unfolded.

Unrestricted and without supporting leg the reusable sky of length the most according to claim 1 penetrates carrier rocket, wherein, in need to having The soft tank of lining, to realize the sealing of storage tank, the soft tank of liner is the column soft tank of an independent axial stretching, bottom it Ring-shaped edge be to be glued on the squab panel of rocket body storage tank, its sidewall (13) be in when without internal pressure corrugation shrink State, after upper and lower cover plates closes, the liquid that the soft tank of liner is poured into backs down, and makes axially to be in the column of extended configuration The end face (14) of soft tank contacts with the antetheca (1) of rocket body storage tank.

Unrestricted and without supporting leg the reusable sky of length the most according to claim 1 penetrates carrier rocket, wherein, in not having The soft tank of lining, is completely dependent on the sealing strip at upper and lower cover plates edge, to realize the sealing of storage tank.