CN109018445A - Moonlet vehicle - Google Patents
Moonlet vehicle Download PDFInfo
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- CN109018445A CN109018445A CN201811061135.3A CN201811061135A CN109018445A CN 109018445 A CN109018445 A CN 109018445A CN 201811061135 A CN201811061135 A CN 201811061135A CN 109018445 A CN109018445 A CN 109018445A
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- 239000004449 solid propellant Substances 0.000 claims abstract description 24
- 239000000843 powder Substances 0.000 claims description 24
- 239000007789 gas Substances 0.000 claims description 15
- IJGRMHOSHXDMSA-UHFFFAOYSA-N Atomic nitrogen Chemical compound N#N IJGRMHOSHXDMSA-UHFFFAOYSA-N 0.000 claims description 14
- 238000002485 combustion reaction Methods 0.000 claims description 10
- 238000005422 blasting Methods 0.000 claims description 8
- 229910052757 nitrogen Inorganic materials 0.000 claims description 7
- 239000007787 solid Substances 0.000 claims 1
- 239000007800 oxidant agent Substances 0.000 abstract description 11
- 239000007788 liquid Substances 0.000 abstract description 9
- 230000008901 benefit Effects 0.000 abstract description 7
- 238000005516 engineering process Methods 0.000 abstract description 5
- 238000002955 isolation Methods 0.000 abstract description 4
- 238000012423 maintenance Methods 0.000 abstract description 4
- 238000000926 separation method Methods 0.000 description 13
- 238000010586 diagram Methods 0.000 description 9
- 230000005520 electrodynamics Effects 0.000 description 7
- 239000000243 solution Substances 0.000 description 6
- MHAJPDPJQMAIIY-UHFFFAOYSA-N Hydrogen peroxide Chemical compound OO MHAJPDPJQMAIIY-UHFFFAOYSA-N 0.000 description 4
- 239000002131 composite material Substances 0.000 description 4
- 238000009434 installation Methods 0.000 description 4
- 229910000838 Al alloy Inorganic materials 0.000 description 3
- 108010066057 cabin-1 Proteins 0.000 description 3
- 238000002156 mixing Methods 0.000 description 3
- NJPPVKZQTLUDBO-UHFFFAOYSA-N novaluron Chemical compound C1=C(Cl)C(OC(F)(F)C(OC(F)(F)F)F)=CC=C1NC(=O)NC(=O)C1=C(F)C=CC=C1F NJPPVKZQTLUDBO-UHFFFAOYSA-N 0.000 description 3
- 238000003860 storage Methods 0.000 description 3
- 229920000049 Carbon (fiber) Polymers 0.000 description 2
- 229920002121 Hydroxyl-terminated polybutadiene Polymers 0.000 description 2
- 239000000956 alloy Substances 0.000 description 2
- XAGFODPZIPBFFR-UHFFFAOYSA-N aluminium Chemical compound [Al] XAGFODPZIPBFFR-UHFFFAOYSA-N 0.000 description 2
- 229910052782 aluminium Inorganic materials 0.000 description 2
- 239000004917 carbon fiber Substances 0.000 description 2
- 230000003197 catalytic effect Effects 0.000 description 2
- 238000006243 chemical reaction Methods 0.000 description 2
- 238000005183 dynamical system Methods 0.000 description 2
- 230000000694 effects Effects 0.000 description 2
- 238000004880 explosion Methods 0.000 description 2
- 229910052739 hydrogen Inorganic materials 0.000 description 2
- 239000011229 interlayer Substances 0.000 description 2
- VNWKTOKETHGBQD-UHFFFAOYSA-N methane Chemical compound C VNWKTOKETHGBQD-UHFFFAOYSA-N 0.000 description 2
- 239000000203 mixture Substances 0.000 description 2
- 230000001590 oxidative effect Effects 0.000 description 2
- 239000003380 propellant Substances 0.000 description 2
- 238000000197 pyrolysis Methods 0.000 description 2
- 230000003014 reinforcing effect Effects 0.000 description 2
- OKTJSMMVPCPJKN-UHFFFAOYSA-N Carbon Chemical compound [C] OKTJSMMVPCPJKN-UHFFFAOYSA-N 0.000 description 1
- 241001061076 Melanonus zugmayeri Species 0.000 description 1
- 229910001069 Ti alloy Inorganic materials 0.000 description 1
- 239000004411 aluminium Substances 0.000 description 1
- 230000009286 beneficial effect Effects 0.000 description 1
- 229910052799 carbon Inorganic materials 0.000 description 1
- 238000006555 catalytic reaction Methods 0.000 description 1
- 150000001875 compounds Chemical class 0.000 description 1
- 238000010276 construction Methods 0.000 description 1
- 125000004122 cyclic group Chemical group 0.000 description 1
- 230000006837 decompression Effects 0.000 description 1
- 239000003814 drug Substances 0.000 description 1
- 230000009977 dual effect Effects 0.000 description 1
- 239000000835 fiber Substances 0.000 description 1
- 239000000945 filler Substances 0.000 description 1
- 238000002347 injection Methods 0.000 description 1
- 239000007924 injection Substances 0.000 description 1
- 239000010410 layer Substances 0.000 description 1
- 239000000463 material Substances 0.000 description 1
- 238000000034 method Methods 0.000 description 1
- 238000012544 monitoring process Methods 0.000 description 1
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- 230000005855 radiation Effects 0.000 description 1
- 238000005096 rolling process Methods 0.000 description 1
Classifications
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64G—COSMONAUTICS; VEHICLES OR EQUIPMENT THEREFOR
- B64G1/00—Cosmonautic vehicles
- B64G1/22—Parts of, or equipment specially adapted for fitting in or to, cosmonautic vehicles
- B64G1/40—Arrangements or adaptations of propulsion systems
- B64G1/403—Solid propellant rocket engines
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64G—COSMONAUTICS; VEHICLES OR EQUIPMENT THEREFOR
- B64G1/00—Cosmonautic vehicles
- B64G1/22—Parts of, or equipment specially adapted for fitting in or to, cosmonautic vehicles
- B64G1/40—Arrangements or adaptations of propulsion systems
- B64G1/403—Solid propellant rocket engines
- B64G1/404—Hybrid rocket engines
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- Engineering & Computer Science (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Remote Sensing (AREA)
- Aviation & Aerospace Engineering (AREA)
- Testing Of Engines (AREA)
Abstract
The present invention relates to field of aerospace technology, more particularly, to a kind of moonlet vehicle.It includes the radome fairing cabin being sequentially connected in series, three sub- grades, two three-level interstages, two sub- grades, a second level interstage, a sub- grade and endpiece；The power of the one sub- grade and the two sub- grade is hybrid rocket engine, and the power of the three sub- grade is solid propellant rocket.Physical isolation before the power of moonlet vehicle provided by the invention, a sub- grade and two sub- grades uses hybrid rocket engine, liquid oxidizer and solid fuel to light a fire, it is highly-safe, reduce guarantee maintenance cost；The power of three sub- grades uses solid propellant rocket, and mass ratio is high, and deadweight is few, in the case of transporting same quality payload, effectively reduces moonlet vehicle scale, improves capability of fast response.Moonlet vehicle provided by the invention can also have capability of fast response while guaranteeing its commercial value and economic benefit.
Description
Technical field
The present invention relates to field of aerospace technology, more particularly, to a kind of moonlet vehicle.
Background technique
Moonlet has many advantages, such as that small in size, light weight and cost is low, the lead time is short, radiation pattern fast and flexible, hair
It penetrates quantity and accounts for more than half total of satellite launch, and this ratio is also being continuously increased.
At present for the requirement of moonlet transmitting, urgent need has the moonlet vehicle of capability of fast response, so as to
Achieve the purpose that gain the initiative in time, rapid pin pair, and while considering commercial value, with greater need for focusing on its low cost
Economic benefit.
That is, how while guaranteeing its commercial value and economic benefit, additionally it is possible to have quick response
Ability is technical problems to be solved needed for existing moonlet vehicle.
Summary of the invention
The purpose of the present invention is to provide a kind of moonlet vehicles, to solve the technical problems existing in the prior art.
Moonlet vehicle provided by the invention, including be sequentially connected in series radome fairing cabin, three sub- grades, two three-level interstages,
Two sub- grades, a second level interstage, a sub- grade and endpiece；
The power of the one sub- grade and the two sub- grade is hybrid rocket engine, and the power of the three sub- grade is
Solid propellant rocket.
Further, the radome fairing cabin includes cover, instrument room and satellite and the rocket separating mechanism；
The instrument room is fixed in the cover；
The satellite and the rocket separating mechanism is arranged on the instrument room, and the instrument room is connect with described three sub- grades.
Further, it is provided with Attitude and orbit control system in described one sub- grade, the two sub- grade and the three sub- grade, for controlling
The flight attitude of rocket processed.
Further, the Attitude and orbit control system includes nitrogen cylinder, high pressure valve, filter, pressure reducing valve, solenoid valve and rail control
Thrust chamber；
The nitrogen cylinder is connect by the high pressure valve with the filter；
The other end of the filter is provided with pressure reducing valve；
The pressure reducing valve is provided with the solenoid valve far from one end of the filter；
The solenoid valve is provided with the rail control thrust chamber far from one end of the pressure reducing valve.
Further, the Attitude and orbit control system in described one sub- grade and the two sub- grade is all made of four thrusters as power；
Attitude and orbit control system in the three sub- grade is using six thrusters as power.
Further, the hybrid rocket engine include the first power gas cylinder, tank, turbine pump, the first powder column,
First motor power room and the first jet pipe；
The first power gas cylinder and the turbine pump are fixed at the tank and first motor power
Between room；
First powder column is arranged in first motor power room；
The one end of first motor power room far from the tank is arranged in first jet pipe.
Further, first jet pipe is gimbaled nozzle.
Further, the solid propellant rocket includes shell, igniter, third powder column and the second jet pipe；
The third powder column is arranged in the shell；
Second jet pipe is connect with the combustion chamber, and second jet pipe and the combustion chamber；
The igniter is connect with the third powder column, for lighting the third powder column.
Further, the two three-levels interstage is cylindrical type or pyramid type；
The one second level interstage is cylindrical type or pyramid type.
Further, pass through between described one sub- grade and the two sub- grade, between the two sub- grade and the three sub- grade
Blasting bolt connection.
The power of moonlet vehicle provided by the invention, a sub- grade and two sub- grades uses hybrid rocket engine,
Physical isolation before liquid oxidizer and solid fuel are lighted a fire, it is highly-safe, reduce guarantee maintenance cost；The power of three sub- grades is adopted
With solid propellant rocket, mass ratio is high, and deadweight is few, in the case of transporting same quality payload, effectively reduces little Wei
Star vehicle scale improves capability of fast response.Moonlet vehicle provided by the invention, can guarantee its commercial value and
While economic benefit, also there is capability of fast response.
Detailed description of the invention
It, below will be to specific in order to illustrate more clearly of the specific embodiment of the invention or technical solution in the prior art
Embodiment or attached drawing needed to be used in the description of the prior art be briefly described, it should be apparent that, it is described below
Attached drawing is some embodiments of the present invention, for those of ordinary skill in the art, before not making the creative labor
It puts, is also possible to obtain other drawings based on these drawings.
The structural schematic diagram of embodiment moonlet vehicle in Fig. 1 present invention；
The structural schematic diagram of embodiment cover in Fig. 2 present invention；
The structural schematic diagram of embodiment instrument room in Fig. 3 present invention；
The structural upright schematic diagram of embodiment three-level solid propellant rocket in Fig. 4 present invention；
The structural upright schematic diagram of embodiment second level hybrid rocket engine in Fig. 5 present invention；
The structural upright schematic diagram of embodiment level-one hybrid rocket engine in Fig. 6 present invention；
Embodiment Attitude and orbit control system schematic diagram in Fig. 7 present invention；
Example scheme trajectory constitutes schematic diagram in Fig. 8 present invention；
Fig. 9-Figure 12 is embodiment overall trajectory Parameter analysis curve in the present invention.
Appended drawing reference:
1: radome fairing cabin；101: cover；102: arrow carries computer；103: remote-measuring equipment；104: inertial navigation equipment；105: installation
Pedestal；106: instrument section structure；
2: three sub- grades；201: combustion chamber；202: third powder column；203: third jet pipe；204: third structural member；
3: two three-level interstages；
4: two sub- grades；401: the second power gas cylinders；402: electrodynamic pump；403: the second motor power rooms；404: the second knots
Component；405: the second jet pipes；406: the second powder columns；
5: one second level interstages；
6: one sub- grades；6011: the first power gas cylinders；6012: tank；6013: turbine pump；6014: the first motor powers
Room；6015: first structure part；6016: the first jet pipes；6017: the first powder columns；6021: nitrogen cylinder；6022: high pressure valve；6023:
Filter；6024: pressure reducing valve；6025: solenoid valve；6026: rail control thrust chamber.
Specific embodiment
Technical solution of the present invention is clearly and completely described below in conjunction with attached drawing, it is clear that described implementation
Example is a part of the embodiment of the present invention, instead of all the embodiments.Based on the embodiments of the present invention, ordinary skill
Personnel's every other embodiment obtained without making creative work, shall fall within the protection scope of the present invention.
In the description of the present invention, it should be noted that term " center ", "upper", "lower", "left", "right", "vertical",
The orientation or positional relationship of the instructions such as "horizontal", "inner", "outside" be based on the orientation or positional relationship shown in the drawings, merely to
Convenient for description the present invention and simplify description, rather than the device or element of indication or suggestion meaning must have a particular orientation,
It is constructed and operated in a specific orientation, therefore is not considered as limiting the invention.
In addition, term " first ", " second ", " third " are used for description purposes only, it is not understood to indicate or imply phase
To importance.
In the description of the present invention, it should be noted that unless otherwise clearly defined and limited, term " installation ", " phase
Even ", " connection " shall be understood in a broad sense, for example, it may be being fixedly connected, may be a detachable connection, or be integrally connected；It can
To be mechanical connection, it is also possible to be electrically connected；It can be directly connected, can also can be indirectly connected through an intermediary
Connection inside two elements.For the ordinary skill in the art, above-mentioned term can be understood at this with concrete condition
Concrete meaning in invention.
As shown in attached drawing 1- Figure 12, the present invention provides a kind of moonlet vehicles, including the radome fairing cabin being sequentially connected in series
1, three sub- grades 2, two three-level interstages 3, two sub- grades 4, a second level interstage 5, a sub- grade 6 and endpiece；One sub- grade 6 and two sub- grades 4
Power be hybrid rocket engine, the power of three sub- grades 2 is solid propellant rocket.
In the present embodiment, carrier rocket rocket body structure is all made of carbon fiber, aluminium alloy, titanium alloy material to reduce structure
Quality passes through flanged joint between each bay section of rocket and engine.
In the present embodiment, the power of a sub- grade 6 and two sub- grades 4 be hybrid rocket engine, three sub- grades 2 it is dynamic
Power is the moonlet vehicle of solid propellant rocket, and 100 kilograms of payload can be transported to the circle of the sun synchronization at 700km
Track.Such setting, high reliablity is low in cost, convenient for quickly assembling rapid fire, it can be achieved that quick response.
In the present embodiment, 23.95 meters of carrier rocket overall length, 1.4 meters of maximum gauge, slenderness ratio 17.1；It takes off quality
22.50 tons, 299.2 thousand Ns of level-one average thrust, thrust ratio of taking off 1.36.
In the present embodiment, moonlet vehicle is laid out using thtee-stage shiplock formula, from arrow top to arrow tail, is followed successively by radome fairing
Cabin 1, three sub- grades 2, two three-level interstages 3, two sub- grades 4, a second level interstage 5, a sub- grade 6 and endpiece.Wherein, a sub- grade 6, two
Sub- grade 4 is all made of the hybrid rocket engine (solid fuel and liquid oxidizer) of composite material, and three sub- grades 2 are using compound
The solid propellant rocket of material.The technical performance of each sub- grade is as shown in the table.
1 basic mechanical design feature of table
In the present embodiment, above-mentioned two three-levels interstage 3 and a second level interstage 5 are interstage section, and major function has been
At the connection between rocket grade, row flame space is provided for earlier stages rocket engine during stage separation.If diameter between two-stage
Unchanged then to use isometrical cylindrical tube shape, structure function is similar with frustum interstage structure.
In the present embodiment, interstage section skeleton equally uses carbon fibre composite or aluminum alloy materials.If between two-stage
Outer diameter variation, then change the form using frustum, internal structure equally uses the form of four reinforcing ribs.
In the present embodiment, to keep diameter change slower, length is appropriately extended using the conical surface of Small Taper, using multistage
Form.
In the present embodiment, interstage section is detached from after the completion of stage separation with later stages, to mitigate flight reappearance.
The effect of above-mentioned endpiece is connection carrier rocket and launcher.
In the present embodiment, endpiece uses carbon fiber composite structure or aluminium alloy structure, by two end flanges and four
Circumferential equally distributed stringer structure composition.
In the present embodiment, to mitigate quality, flange and stringer structure are thin-walled hollow structure, central filler aluminum honeycomb
Interlayer or foamed aluminium, under the premise of proof strength and rigidity, by lighter quality can complete support whole rocket and effectively
Load, that is, moment of flexure synergy caused by the all-mass and wind load of load.
In the present embodiment, axle power and moment of flexure (being converted into axle power) are by emitting support with 4 and the shape of the above concentrated force
Formula is transmitted on endpiece.
In the present embodiment, the design point of endpiece is set according to the maximum duty under the various operating conditions totally provided
Meter, it is highly preferred that being designed in the state that rocket is erect.
Preferred embodiment is that radome fairing cabin 1 includes cover 101, instrument room and satellite and the rocket separating mechanism；Instrument room is fixed
It is arranged in cover 101；Satellite and the rocket separating mechanism is arranged on instrument room, and instrument room is connect with three sub- grades 2.
As shown in Figures 2 and 3, in the present embodiment, radome fairing cabin 1 include cover 101, payload, satellite and the rocket separating mechanism,
Instrument room.
The main task of above-mentioned cover 101 is that payload and electrical equipment safely pass through dense atmosphere in protective cover
Layer, structure are followed successively by cone section and cylindrical section from front to back.
In the present embodiment, to mitigate quality, the various pieces of cover 101 are all made of sandwich, and ectonexine is thin
Wall shell, inside and outside interlayer are evenly distributed with longitudinal and transverse direction reinforcing rib and reinforce its structural strength and rigidity.
In the present embodiment, it will be disposed after 101 completion task of cover, and be decomposed into two valves when throwing cover, while to rocket body two
Side, which is released, is detached from rocket body.Aforementioned cover 101 is arranged lateral separation face and is longitudinally separated face, and lateral separation face is located at bottom, uses
Blasting bolt connection is longitudinally separated face for cover 101 and is divided into two and half covers, and two and half covers pass through longitudinal unlocking mechanism connection.
The payload fairing shape is cone-cylindricality, is connected as instrument room with payload.
Control system, telemetry system grade other electrical systems are installed in instrument room.Instrument room is cylindrical structure, on
Portion is equipped with payload attachment device, and payload is connected by instrument room with rocket.
Instrument room includes that arrow carries computer 102, remote-measuring equipment 103, inertial navigation equipment 104, installation pedestal 105 and instrument cabin
Structure 106, arrow carry computer 102, remote-measuring equipment 103 and inertial navigation equipment 104 and are connected to instrument by extraction-type installation pedestal 105
On device section structure 106.
It is provided with one-stage rocket engine and level-one Attitude and orbit control system in one sub- grade 6, and is connected with endpiece；In two sub- grades 4
It is provided with booster-missile combination engine and second level Attitude and orbit control system；Three-stage rocket engine and rail control system are provided in three sub- grades 2
System.
Preferred embodiment is that Attitude and orbit control system includes nitrogen cylinder 6021, high pressure valve 6022, filter 6023, decompression
Valve 6024, solenoid valve 6025 and rail control thrust chamber 6026；Nitrogen cylinder 6021 is connect by high pressure valve 6022 with filter 6023；
The other end of filter 6023 is provided with pressure reducing valve 6024；Pressure reducing valve 6024 is provided with solenoid valve far from one end of filter 6023
6025；Solenoid valve 6025 is provided with rail control thrust chamber 6026 far from one end of pressure reducing valve 6024.
In the present embodiment, Attitude and orbit control system, three appearance rails are respectively arranged in a sub- grade 6, two sub- grades 4 and three sub- grades 2
The structure of control system is identical.
In the present embodiment, the corresponding rail control thrust chamber 6026 of a solenoid valve 6025, forms one group of thruster.
In the present embodiment, Attitude and orbit control systems at different levels include four groups or more thrusters, to meet rolling demand for control.It is excellent
Selection of land realizes that the multiple degrees of freedom of rocket posture is adjusted, level-one Attitude and orbit control system, second-level attitude in the case where considering least construction weight
Rail control system uses four thruster schemes, and three-level Attitude and orbit control system uses six thruster schemes.
Fig. 8 be embodiment moonlet vehicle in the present invention project trajectory constitute schematic diagram, main inflight phase, including
Take off vertically a section P01, pitchover section P02, zero-incidence inflight phase P03, side program pitch angle inflight phase P04, vacuum gliding
Section P05, three-level program pitch angle inflight phase P06.
After one-stage rocket engine ignition, whole rocket starts section P01 that takes off vertically, and enters pitchover section after a certain time
P02；It is transferred to zero-incidence inflight phase P03 after pitchover section P02, guarantees that aerodynamic drag is small, energy loss is low.Zero-incidence flies
One-stage rocket engine cutoff after row section P03, interstage section separating mechanism reliably working keep a sub- grade 6 and two sub- grades 4 reliable
Separation；Booster-missile combination engine ignition after the completion of separation, into side program pitch angle inflight phase P04, until shutdown and three sons
2 reliable separations of grade；Three-stage rocket engine ignition and three-level program pitch angle inflight phase is carried out after vacuum gliding section P05
Payload is sent into predetermined release altitude and discharged by P06.Vacuum gliding section P05, three-level program pitch angle inflight phase
P06 is flown using three-level attitude control engine Map and image database, guarantees the accuracy entered the orbit.
Preferably, by optimized trajectory design, guarantee to choose a trajectory, save energy most.Timing after optimization is as follows
Shown in table.Wherein, it is pitchover section P02 between serial number 1-2 to take off vertically a section P01 between serial number 0-1, is zero to attack between serial number 2-3
It is side program pitch angle inflight phase P04 between angle inflight phase P03, serial number 4-5, is vacuum gliding section P05, serial number between serial number 5-6
It is three-level program pitch angle inflight phase P06 between 6-7.
3 project trajectory flight time sequence of table
It is embodiment overall trajectory Parameter analysis curve in the present invention, including the angle of attack-time graph shown in Fig. 9-Figure 12
C1, speed-time curve C2, trajectory tilt angle-time graph C3, height-time graph C4.
The above-mentioned angle of attack-time graph C1 only takes two flight courses of section P01 and pitchover section P02 that take off vertically, preferably
Ground designs the maximum angle of attack and is no more than 3 °, to guarantee that pneumatic stress is good.
Above-mentioned speed-time curve C2, including level-one active section C201, secondary work section C202, unpowered gliding section
C203, three-level active section C204.Wherein, level-one active section C201 corresponding take off vertically a section P01, pitchover section P02 and zero is attacked
Angle inflight phase P03, secondary work section C202, unpowered gliding section C203, three-level active section C204 respectively correspond side program and bow
Elevation angle inflight phase P04, vacuum gliding section P05, three-level program pitch angle inflight phase P06.
Preferably, from taking off to release payload, design total duration is no more than 700 seconds.
In above-mentioned trajectory tilt angle-time graph C3, the part of the corresponding section P01 that takes off vertically, trajectory tilt angle is remained
90°。
Preferably, trajectory tilt angle is 0 ° at payload point of release, indicates the scheduled standard round for being 0 into eccentricity
Track.
Preferably, design variation rate is per second no more than 5 ° in 50 seconds after trajectory tilt angle, to guarantee payload with smaller angle
Speed enters planned orbit, improves orbit injection accuracy, because of the issuable additional angular momentum of angular speed when reducing release payload.
In above-mentioned height-time graph C4, launch point mutually a height of 0 is set, final payload release point height is
700km。
Pay special attention to ground, ordinate height is phase of the moonlet vehicle away from launch point height above sea level in height-time graph C4
To height.
Preferred embodiment is that the hybrid rocket engine used in a sub- grade 6 includes the first power gas cylinder
6011, tank 6012, turbine pump 6013, the first powder column 6017, the first motor power room 6014 and the first jet pipe 6015；Power
Gas cylinder 6011 and turbine pump 6013 are fixed between tank 6012 and the first motor power room 6014；First powder column
6017 are arranged in the first motor power room 6014；The setting of first jet pipe 6015 is in the first motor power room 6014 far from storage
One end of case 6012.
The hybrid rocket engine used in two sub- grades 4 includes 401 electrodynamic pump 402, second of the second power gas cylinder
Powder column 406, the second motor power room 403, the second jet pipe 405 and the second structural member 404.
In the present embodiment, the first jet pipe 6015 and the second jet pipe 405 are gimbaled nozzle.
In the present embodiment, solid propellant rocket includes shell, igniter, third powder column 202 and third jet pipe 203；
The third powder column 202 is arranged in the shell；The third jet pipe 206 is connect with the combustion chamber 201, and the third
Jet pipe 203 is connected to the combustion chamber 201；The igniter is connect with the third powder column 202, for lighting the third medicine
Column 202.
One-stage rocket engine is the 98%H that thruster vector control is carried out using gimbaled nozzle2O2The mixing of/HTPB base solid-liquid
Rocket engine, is combined using the propellant of solid fuel and liquid oxidizer, and engine diameters 1.4m, the course of work averagely pushes away
Power 299.2kN, working time 140s.One sub- 6 transportation systems of grade, that is, oxidant delivery system, is followed using full flow turbine pump 6013
Loop system, oxidants hydrogen peroxide deliver into pump under storage pressure extruding, by dividing after flowing out in pump through catalytic bed catalysis
Solution is high-temperature mixed gas, and high-temperature gas burns into combustion chamber 201 is interior with the blending of solid fuel pyrolysis gas after driving turbine.
Booster-missile combination engine is similarly the 98%H that thruster vector control is carried out using gimbaled nozzle2O2/ HTPB base solid-liquid
Hybrid rocket engine, is combined using the propellant of solid fuel and liquid oxidizer, and engine diameters 1.1m, vacuum averagely pushes away
Power 66.1kN, working time 150s.Two sub- 4 transportation systems of grade, that is, oxidant delivery systems, using 402 cyclic system of dual stage electrodynamic pump
System, oxidants hydrogen peroxide deliver into electrodynamic pump 402 under storage pressure extruding, deliver into after the pressurization of electrodynamic pump 402
It burns in combustion chamber 201 with the blending of solid fuel pyrolysis gas.
Three-stage rocket engine is the solid propellant rocket that thruster vector control is carried out using gimbaled nozzle, engine direct
Diameter 1.1m, vacuum average thrust 28.2kN, working time 80s.
Moonlet vehicle dynamical system overall plan is as shown in the table.
2 dynamical system overall plan of table
In the present embodiment, hybrid rocket engine includes the first power gas cylinder 6011, tank 6012, turbine pump
6013, the first motor power room 6014, the first jet pipe 6015 and first structure part 6015.Wherein, the first power gas cylinder 6011
It is placed in the centre of tank 6012 and the first motor power room 6014, to save space.
In the present embodiment, turbine pump 6013 includes pump and catalytic chamber two parts, in the first motor power room 6014
First powder column 6017 is wheel hole shape, the first jet pipe 6015 is gimbaled nozzle.
In the present embodiment, solid propellant rocket includes combustion chamber 201, igniter, third powder column 202, third jet pipe
203 and third structural member 204.Wherein, igniter does not mark in figure.
In the present embodiment, third powder column 202 is cabane type, and third jet pipe 203 is gimbaled nozzle.
Preferred embodiment is that two three-level interstages 3 are cylindrical type or pyramid type；One second level interstage 5 is cylindrical type
Or pyramid type.
It is connected between one sub- grade 6, two sub- grades 4 using blasting bolt, thermal release mode；It is adopted between two sub- grades 4 and three sub- grades 2
It is connected with blasting bolt, cold separate mode；It is connected between three sub- grades 2 and payload using blasting bolt, cold separate mode.
Payload is longitudinally separated face using pollution-free explosion locking device, provides the lateral separation energy while unlock.
The lateral separation face of radome fairing is made of one group of blasting bolt and cut spring, and the vertical, horizontal parting surface of radome fairing unlocks simultaneously,
The separation energy makes radome fairing realize rotation throwing formula separation.
The working principle of the invention is:
Moonlet vehicle using horizontal general assembly, horizontal checkout, horizontal transport " three flat surveys hair modes ", by motor vehicle turn
Be transported to launch point and rise it is perpendicular after, car launcher is withdrawn, and is adjusted posture, is emitted.
Moonlet vehicle transmitting after, one-stage rocket engine taken off vertically section, the pitchover stage, zero-incidence flight
Section reaches certain altitude and speed, and interstage section blasting bolt works after shutdown, and it is small that a second level separates one under aerodynamic drag effect
Section distance.2s after first class engine separation, the work of booster-missile combination engine ignition, the thrust that jet pipe generates push a sub- grade 6 open,
Realize thermal release.Enter program pitch angle state of flight by the scheme booster-missile combination engine of bookbinding, passes through carrier rocket/ground
Data-link, ground control station implement flight course monitoring, trajectory modifying, shut down after work, two three-level interstage sections explosion spiral shell
Bolt work, realizes cold separation between grade, into gliding section.Cold air reaction device, which is started to work, during gliding adjusts track, knot
Three-stage rocket engine ignition after beam, while payload being held position with 3 axis under the amendment of cold air reaction device and is given
Enter planned orbit, payload relieving mechanism discharges payload, completes carrier rocket and all works.
The beneficial effects of the present invention are:
1. in a second level hybrid rocket engine, physical isolation before liquid oxidizer and solid fuel igniting, safety
Property it is high, reduce guarantee maintenance cost.
2. using 402 transportation system of electrodynamic pump, 402 supply system of electrodynamic pump is with inexpensive, system is simple, tank 6012
The advantages such as pressure is low, architecture quality is light, variable thrust range is big, operating mode is flexible.
3. the composite material using light-high-strength makes aircraft, weight is greatly reduced, consuming energy is few, transmitting boat
It is rocket-powered needed for its device to greatly reduce.
4. three-level solid propellant rocket mass ratio is high, deadweight is few, in the case of transporting same quality payload, effectively
Reduce moonlet vehicle scale.
The power of moonlet vehicle provided by the invention, a sub- grade 6 and two sub- grades 4 is started using hybrid rocket
Physical isolation before machine, liquid oxidizer and solid fuel are lighted a fire, it is highly-safe, reduce guarantee maintenance cost；Three sub- grades 2 are moved
Power uses solid propellant rocket, and mass ratio is high, and deadweight is few, in the case of transporting same quality payload, effectively reduces
Moonlet vehicle scale improves capability of fast response.Moonlet vehicle provided by the invention can guarantee its business valence
While value and economic benefit, also there is capability of fast response.
Finally, it should be noted that the above embodiments are only used to illustrate the technical solution of the present invention., rather than its limitations；To the greatest extent
Pipe present invention has been described in detail with reference to the aforementioned embodiments, those skilled in the art should understand that: its according to
So be possible to modify the technical solutions described in the foregoing embodiments, or to some or all of the technical features into
Row equivalent replacement；And these are modified or replaceed, various embodiments of the present invention technology that it does not separate the essence of the corresponding technical solution
The range of scheme.
In addition, it will be appreciated by those of skill in the art that although some embodiments in this include institute in other embodiments
Including certain features rather than other feature, but the combination of the feature of different embodiment means in the scope of the present invention
Within and form different embodiments.For example, in claims above, embodiment claimed it is any it
One can in any combination mode come using.The information disclosed in the background technology section is intended only to deepen to the present invention
General background technology understanding, and be not construed as recognizing or imply that information composition has been this field skill in any form
The prior art well known to art personnel.
Claims (10)
1. a kind of moonlet vehicle, which is characterized in that including be sequentially connected in series radome fairing cabin, three sub- grades, two three-level interstages,
Two sub- grades, a second level interstage, a sub- grade and endpiece；
The power of the one sub- grade and the two sub- grade is hybrid rocket engine, and the power of the three sub- grade is solid
Rocket engine.
2. moonlet vehicle according to claim 1, which is characterized in that the radome fairing cabin includes cover, instrument room
With satellite and the rocket separating mechanism；
The instrument room is fixed in the cover；
The satellite and the rocket separating mechanism is arranged on the instrument room, and the instrument room is connect with described three sub- grades.
3. moonlet vehicle according to claim 1, which is characterized in that a sub- grade, the two sub- grade and described
It is provided with Attitude and orbit control system in three sub- grades, for controlling the flight attitude of rocket.
4. moonlet vehicle according to claim 3, which is characterized in that the Attitude and orbit control system includes nitrogen cylinder, height
Pressure valve, filter, pressure reducing valve, solenoid valve and rail control thrust chamber；
The nitrogen cylinder is connect by the high pressure valve with the filter；
The other end of the filter is provided with pressure reducing valve；
The pressure reducing valve is provided with the solenoid valve far from one end of the filter；
The solenoid valve is provided with the rail control thrust chamber far from one end of the pressure reducing valve.
5. moonlet vehicle according to claim 3, which is characterized in that the appearance in a sub- grade and the two sub- grade
Rail control system is all made of four thrusters as power；
Attitude and orbit control system in the three sub- grade is using six thrusters as power.
6. moonlet vehicle according to claim 1, which is characterized in that the hybrid rocket engine includes the
One power gas cylinder, tank, turbine pump, the first powder column, the first motor power room and the first jet pipe；
The first power gas cylinder and the turbine pump be fixed at the tank and first motor power room it
Between；
First powder column is arranged in first motor power room；
The one end of first motor power room far from the tank is arranged in first jet pipe.
7. moonlet vehicle according to claim 6, which is characterized in that first jet pipe is gimbaled nozzle.
8. moonlet vehicle according to claim 1, which is characterized in that the solid propellant rocket include shell,
Igniter, third powder column and third jet pipe；
The third powder column is arranged in the shell；
The third jet pipe is connect with the combustion chamber, and the third jet pipe and the combustion chamber；
The igniter is connect with the third powder column, for lighting the third powder column.
9. moonlet vehicle according to claim 1, which is characterized in that the two three-levels interstage is cylindrical type or circle
It is tapered；
The one second level interstage is cylindrical type or pyramid type.
10. moonlet vehicle according to claim 1, which is characterized in that between a sub- grade and the two sub- grade,
It is connected by blasting bolt between the two sub- grade and the three sub- grade.
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| CN201811061135.3A CN109018445B (en) | 2018-09-12 | 2018-09-12 | Small satellite carrier |
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|---|---|---|---|
| CN201811061135.3A CN109018445B (en) | 2018-09-12 | 2018-09-12 | Small satellite carrier |
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| CN109018445B CN109018445B (en) | 2020-11-17 |
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| CN109707538A (en) * | 2019-01-10 | 2019-05-03 | 北京航空航天大学 | The sub- grade of the one of rocket and rocket |
| CN110435934A (en) * | 2019-07-19 | 2019-11-12 | 西北工业大学 | A kind of reusable inert satellite recovery flight device |
| CN110775301A (en) * | 2019-12-04 | 2020-02-11 | 哈尔滨工业大学 | Aircraft with high rail-entering efficiency and strong maneuvering capability and rail-entering method thereof |
| CN111927997A (en) * | 2020-08-31 | 2020-11-13 | 蓝箭航天空间科技股份有限公司 | Space engine with structure optimization relief pressure valve |
| CN112115551A (en) * | 2020-09-11 | 2020-12-22 | 北京星途探索科技有限公司 | Prediction method for interstage thermal separation motion of carrier rocket |
| CN112412659A (en) * | 2020-11-05 | 2021-02-26 | 北京空天技术研究所 | Integrated configuration of interstage connecting section of aircraft and front seal head of booster |
| CN112432564A (en) * | 2020-11-13 | 2021-03-02 | 北京宇航系统工程研究所 | General stage section structure suitable for control of carrier rocket landing zone |
| CN112611269A (en) * | 2021-02-04 | 2021-04-06 | 北京星际荣耀空间科技股份有限公司 | Carrier rocket |
| CN113670618A (en) * | 2021-06-10 | 2021-11-19 | 北京星途探索科技有限公司 | Sounding rocket carrying solid-liquid hybrid engine test |
| CN114659415A (en) * | 2022-03-01 | 2022-06-24 | 航天科工火箭技术有限公司 | Lightweight cabin section structure of carrier |
| CN114858011A (en) * | 2022-07-05 | 2022-08-05 | 星河动力(北京)空间科技有限公司 | Carrier rocket |
| CN114859956A (en) * | 2022-07-05 | 2022-08-05 | 星河动力(北京)空间科技有限公司 | Control method, device and equipment of carrier rocket and storage medium |
| CN115614181A (en) * | 2022-10-21 | 2023-01-17 | 精易兴航(北京)科技创新有限公司 | Simplified configuration power system capable of recycling rocket and rocket thereof |
| CN116929159A (en) * | 2023-09-18 | 2023-10-24 | 北京星河动力装备科技有限公司 | Carrier rocket with solid-liquid hybrid power and launching method thereof |
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| CN109707538A (en) * | 2019-01-10 | 2019-05-03 | 北京航空航天大学 | The sub- grade of the one of rocket and rocket |
| CN110435934A (en) * | 2019-07-19 | 2019-11-12 | 西北工业大学 | A kind of reusable inert satellite recovery flight device |
| CN110435934B (en) * | 2019-07-19 | 2021-02-19 | 西北工业大学 | Reusable invalid satellite recovery aircraft |
| CN110775301A (en) * | 2019-12-04 | 2020-02-11 | 哈尔滨工业大学 | Aircraft with high rail-entering efficiency and strong maneuvering capability and rail-entering method thereof |
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| CN112115551A (en) * | 2020-09-11 | 2020-12-22 | 北京星途探索科技有限公司 | Prediction method for interstage thermal separation motion of carrier rocket |
| CN112412659B (en) * | 2020-11-05 | 2021-12-10 | 北京空天技术研究所 | Integrated structure of interstage connecting section of aircraft and front seal head of booster |
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| CN112611269A (en) * | 2021-02-04 | 2021-04-06 | 北京星际荣耀空间科技股份有限公司 | Carrier rocket |
| CN113670618A (en) * | 2021-06-10 | 2021-11-19 | 北京星途探索科技有限公司 | Sounding rocket carrying solid-liquid hybrid engine test |
| CN114659415A (en) * | 2022-03-01 | 2022-06-24 | 航天科工火箭技术有限公司 | Lightweight cabin section structure of carrier |
| CN114659415B (en) * | 2022-03-01 | 2024-02-09 | 航天科工火箭技术有限公司 | Light cabin section structure of carrier |
| CN114859956A (en) * | 2022-07-05 | 2022-08-05 | 星河动力(北京)空间科技有限公司 | Control method, device and equipment of carrier rocket and storage medium |
| CN114859956B (en) * | 2022-07-05 | 2022-11-18 | 星河动力(北京)空间科技有限公司 | Control method, device and equipment of carrier rocket and storage medium |
| CN114858011A (en) * | 2022-07-05 | 2022-08-05 | 星河动力(北京)空间科技有限公司 | Carrier rocket |
| CN115614181A (en) * | 2022-10-21 | 2023-01-17 | 精易兴航(北京)科技创新有限公司 | Simplified configuration power system capable of recycling rocket and rocket thereof |
| CN115614181B (en) * | 2022-10-21 | 2023-03-07 | 精易兴航(北京)科技创新有限公司 | Simplified configuration power system capable of recycling rocket and rocket thereof |
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