CN108423196A - The two-stage that the first order can be reused is entered the orbit the method for entering the orbit of spacecraft - Google Patents

The two-stage that the first order can be reused is entered the orbit the method for entering the orbit of spacecraft Download PDF

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Publication number
CN108423196A
CN108423196A CN201810305687.8A CN201810305687A CN108423196A CN 108423196 A CN108423196 A CN 108423196A CN 201810305687 A CN201810305687 A CN 201810305687A CN 108423196 A CN108423196 A CN 108423196A
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level
orbit
aircraft
indicates
stage
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聂万胜
杨新垒
宋强
王辉
王迪
赵家丰
王海青
石天
石天一
苏凌宇
侯志勇
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Peoples Liberation Army Strategic Support Force Aerospace Engineering University
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Peoples Liberation Army Strategic Support Force Aerospace Engineering University
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    • 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
    • B64G1/24—Guiding or controlling apparatus, e.g. for attitude control
    • B64G1/242—Orbits and trajectories

Abstract

Enter the orbit the invention discloses the two-stage that a kind of first order can be reused the method for entering the orbit of spacecraft, including step 1, two-stage is entered the orbit the model construction of spacecraft：The first order is sky tower, using SABRE engines as power plant；The second level is pencil rocket, and payload accounts for the 5.89% of gross mass of taking off；Step 2, level-one section of taking off；Step 3, level-one air-breathing mode section rises to 25km with air-breathing mode；Step 4, one-stage rocket schema section, SABRE engines are switched to rocket mode and two-stage spacecraft of entering the orbit are pushed to continue to rise to 100km, the first order and second level separation, and the mode for gliding that the first order is unpowered, which returns to ground, to be realized and reuse；Step 5, the two level section second level of climbing is climbed vertically, and payload is sent into the LEO of 300km with the speed more than 7700m/s.The present invention is based on SABRE engines on the basis of considering technical difficulty and launch cost, realizes that two-stage is entered the orbit, and the first order can be reused；And payload is made to obviously increase.

Description

The two-stage that the first order can be reused is entered the orbit the method for entering the orbit of spacecraft
Technical field
The present invention relates to the technical field of entering the orbit of spacecraft, two-stage that especially a kind of first order can be reused is entered the orbit boat The method of entering the orbit of its device.
Background technology
The collaboration suction type rocket that reaction engineering Co., Ltd of Britain (Reaction Engine Ltd, REL) proposes starts Machine (SynergeticAir-BreathingRocketEngine, SABRE) be it is a kind of using cryogenic media to incoming air carry out Cooling precooling class combined cycle engine, is formed by turbogenerator, rocket engine and punching engine organic assembling.Collection Conjunction has the advantages of rocket engine thrust-weight ratio is high, working range is wide and turbogenerator ratio is leapt high, and has two kinds of air-breathing and rocket Operating mode is expected to enter the orbit as single-stage/multistage, the novel power device of reusable sky and space plane.
Single Stage To Orbit can substantially reduce launch cost, but implement more difficulty, and main cause is by a large amount of structure Quality brings space into, and the requirement to structural coefficient is extremely stringent.Multistage, which is entered the orbit, constantly abandons the architecture quality of failure, implements It is relatively simple, but bring the rising of cost.
It proposes a kind of two-stage the present invention is based on SABRE engines and enters the orbit scheme, give aerospace craft dynamic model And aerodynamic model；The equation of motion is established stage by stage and carries out Study on Numerical Simulation, as a result analytical technology feasibility can be China Carry out based on precooling class combined cycle engine enter the orbit project study provide reference.
Invention content
In view of the above-mentioned deficiencies of the prior art, the technical problem to be solved by the present invention is to provide a kind of first order to repeat The two-stage used is entered the orbit the method for entering the orbit of spacecraft, and the enter the orbit method of entering the orbit of spacecraft of the two-stage which can reuse exists On the basis of considering technical difficulty and launch cost, SABRE engines are based on, realize that two-stage is entered the orbit, and the first order can weigh It is multiple to use；In addition, under the premise of initial take-off mass conservation, payload can be made to obviously increase, and technical difficulty is low.
In order to solve the above technical problems, the technical solution adopted by the present invention is：
A kind of two-stage that the first order can be reused is entered the orbit the method for entering the orbit of spacecraft, and is included the following steps.
Step 1, two-stage is entered the orbit the model construction of spacecraft：Two-stage spacecraft of entering the orbit includes the first order and the second level；First Grade is configured as sky tower, using SABRE engines as power plant；The second level is pencil rocket, using liquid hydrogen/oxygen rocket Engine is as power plant；Payload in the second level accounts for the 5.89% of gross mass of taking off.
Step 2, level-one section of taking off：Two-stage enters the orbit spacecraft near terrestrial equator, and ground is left with fixed elevation θ, and one The flight time of grade section of taking off is t1.
Step 3, level-one air-breathing mode section：After level-one section of taking off, under the action of gravity, aerodynamic force and thrust, with Air-breathing mode rises to the height not less than 25km, and the flight time of level-one air-breathing mode section is t2.
Step 4, one-stage rocket schema section：After level-one air-breathing mode section, SABRE engines are switched to rocket mode simultaneously Two-stage spacecraft of entering the orbit is pushed to continue to climb, after the height for reaching 100km, the first order and second level separation, the first order is unpowered The mode of gliding returns to ground and realizes reuse；The flight time of one-stage rocket schema section is t3.
Step 5, two level is climbed section：After the first order and second level separation, the second level is climbed vertically, and is carried out in Trajectory-terminal Gravity is turned, and payload is sent into the LEO of 300km with the speed more than 7700m/s；Two level is climbed the flight of section Time is t4.
In step 3, when being in level-one air-breathing mode section, the thrust of SABRE engines rises with height and is increased；Step 4 In, when being in one-stage rocket schema section, the thrust of SABRE engines remains unchanged.
In step 2, the equation of motion of level-one section of taking off is expressed as follows：
In formula：V indicates aircraft speed；T indicates motor power suffered by aircraft when in level-one section of taking off；D is indicated Aerodynamic drag suffered by aircraft；F indicates ground friction resistance suffered by aircraft；L indicates aerodynamic lift suffered by aircraft；M is indicated Vehicle mass；m0Indicate mass of loaded vehicle；Indicate aircraft fuel wear rate；ρ indicates that aircraft present position is big Air tightness；S indicates aircraft feature area；CDIndicate aircraft resistance coefficient；CLIndicate aircraft lift coefficient；F indicates ground Friction coefficient；W indicates gravity suffered by aircraft；X indicates aircraft horizontal displacement.
In step 3, the equation of motion of level-one air-breathing mode section indicates as follows：
Wherein,
In formula, T indicates the motor power suffered by aircraft when in level-one air-breathing mode section；m1It indicates to inhale in level-one The initial gross mass of aircraft when gas schema section；Indicate aircraft fuel wear rate；G0 indicates that earth surface gravity accelerates Degree；K indicates lift resistance ratio coefficient；L indicates aerodynamic lift suffered by aircraft；D indicates aerodynamic drag suffered by aircraft；CLIndicate flight Device lift coefficient；CDIndicate aircraft resistance coefficient.
In step 4, the equation of motion of one-stage rocket schema section indicates as follows：
Wherein,
In formula, T indicates the motor power suffered by aircraft when in one-stage rocket schema section；m1It indicates in level-one fire The initial gross mass of aircraft when arrow schema section；Indicate aircraft fuel wear rate；g0, R, H indicate earth surface weight respectively The residing height of power acceleration, earth radius and aircraft；K indicates lift resistance ratio coefficient；L indicates flight vehicle aerodynamic lift；D indicates to fly Aerodynamic drag suffered by row device；CLIndicate aircraft lift coefficient；CDIndicate aircraft resistance coefficient；θ indicates the aircraft angle of attack.
In step 5, two level climb section the equation of motion indicate it is as follows：
In formula：Motor power suffered by aircraft when T indicates to climb section in two level；W indicates gravity suffered by aircraft；m2 Indicate the initial gross mass of aircraft when rocket mode rises at 100km；Indicate fuel consumption flow；Isp expressions liquid oxygen/ Hydrogen rocket specific impulse.
T1=46s, t2=385s, t3=304s, t4=33s, total flight time 768s.
In step 5, the second level is climbed vertically, and carries out gravity turning in Trajectory-terminal, and with the speed of 7925.009m/s Payload is sent into the LEO of 300km.
In step 1, the second level is used as power plant using liquid hydrogen/oxygen rocket engine, the height residing for the rocket engine After degree is higher than the design height of jet pipe, specific impulse will stay in that vacuum specific impulse and numerical value no longer changes；The vacuum specific impulse of hydrogen-oxygen rocket For 4500m/s, rocket engine thrust is controlled by adjusting fuel flow rate in flight course.
The present invention has the advantages that：
(1) when aircraft reaches the orbit altitude of 300km, speed 7909.964m/s meets speed requirement of entering the orbit, Achievable two-stage is entered the orbit.
(2) aircraft takeoff gross weight 345t, payload 20.305t.First order weight 289.98t, structural coefficient are 0.1902.Second level weight 55.038t, structural coefficient 0.12.
(3) compared with the Single Stage To Orbit scheme based on SABRE engines, payload mass score is increased to from 3.74% 5.89%, the launch cost of unit mass payload can be effectively reduced, and technically easy to implement.
Description of the drawings
Fig. 1 shows thrust schematic diagram of the SABRE engines under different height.
Fig. 2 shows that lift resistance ratio is with the change schematic diagram of the angle of attack under different Mach number.
Fig. 3 shows the force analysis figure of level-one section of taking off aircraft.
Fig. 4 shows the force analysis figure of level-one air-breathing mode section.
Fig. 5 shows that two level is climbed the force analysis figure of section aircraft.
Fig. 6 shows that acceleration changes with time in aircraft uphill process.
Fig. 7 shows that aircraft uphill process medium velocity changes with time.
Fig. 8 shows that horizontal displacement changes with time in aircraft uphill process.
Fig. 9 shows that vertical displacement changes with time in aircraft uphill process.
Figure 10 shows that two-stage spacecraft of entering the orbit is entered the orbit process sectional view.
Specific implementation mode
The present invention is described in further detail with specific better embodiment below in conjunction with the accompanying drawings.
As shown in Figure 10, the two-stage that a kind of first order can be reused is entered the orbit the method for entering the orbit of spacecraft, including is walked as follows Suddenly.
Step 1, two-stage is entered the orbit the model construction of spacecraft.
Two-stage is entered the orbit spacecraft, and also referred to as aircraft, the gross mass of aircraft include architecture quality, promote in the present invention Agent quality and payload.According to the architecture quality of aircraft, and then acquire structural coefficient.
Two-stage spacecraft of entering the orbit includes the first order and the second level in series or in parallel with each other, in the present invention, the first order and the Two level is preferably connected in parallel.The gross mass of taking off of aircraft is preferably 345t in the present invention.
The first order is configured as sky tower, uses SABRE engines as power plant.
The aerodynamic parameter of the first order is combined and obtains according to CFD emulation and engineering method, as shown in Figure 2.It can from Fig. 2 To find out, maximum lift-drag ratio is 9 under subsonic speed state, and maximum lift-drag ratio is 5 under Mach 2 ship 2Ma states, less than consonance Supersonic Maximum lift-drag ratio (maximum lift-drag ratio is 7 under consonance Concord 2Ma states) under fast passenger plane 2Ma states, shown in definition graph 2 Aerodynamic parameter in theoretical analysis level be correct.
In addition, the structural coefficient of the first order be preferably 0.1902 namely the first order architecture quality be 65.602t.
According to engine total propellant consumption, propellant can be acquired in the working time in each stage and propellant flow rate Consume gross mass mtCalculation formula it is as follows：
It is acquired according to formula (9), propellant expenditure gross mass is 224.362t in the first order.
The second level is pencil rocket, using liquid hydrogen/oxygen rocket engine as power plant, residing for rocket engine After height is higher than the design height of jet pipe, specific impulse will stay in that vacuum specific impulse and numerical value no longer changes；The vacuum ratio of hydrogen-oxygen rocket Punching is preferably 4500m/s, and the thrust of rocket engine is controlled by adjusting fuel flow rate in flight course.
The initial gross mass of the second level is preferably 55.038t, and the structural coefficient of the second level is preferably 0.12 namely the second level Architecture quality be 6.605t, according to formula (9), it is 28.128t that can acquire in the second level propellant expenditure gross mass.Thus, The payload mass that can be acquired in the second level is 20.305t, accounts for the 5.89% of gross mass of taking off.
In the prior art using SABRE engines as " sky tower " single stage orbit to orbit vehicle of power, quality of taking off is 275t, Design payload is 10.275t, accounts for the 3.74% of gross mass of taking off.Therefore, compared with prior art, proposed by the present invention two Grade enter spacecraft method of entering the orbit can make payload mass (score) obviously increase namely payload mass score from 3.74% has been increased to 5.89%, while technical difficulty lowers significantly, may be implemented in a short time, has larger advantage.
Step 2, level-one section of taking off：Two-stage enters the orbit spacecraft near terrestrial equator, with fixed elevation θ, with about 0.5 horse Conspicuous speed leaves ground, and the flight time of level-one section of taking off is t1, and t1 is preferably 46s.In level-one section of taking off, aircraft by The effect of gravity, aerodynamic force and ground friction resistance, horizontal under the action of bonding force to accelerate, force analysis is as shown in Figure 3.
The equation of motion of level-one section of taking off is expressed as follows：
In formula：V indicates aircraft speed；T indicates motor power suffered by aircraft when in level-one section of taking off；D is indicated Aerodynamic drag suffered by aircraft；F indicates ground friction resistance suffered by aircraft；L indicates aerodynamic lift suffered by aircraft；M is indicated Vehicle mass；m0Indicate mass of loaded vehicle；Indicate aircraft fuel wear rate；ρ indicates that aircraft present position is big Air tightness；S indicates aircraft feature area；CDIndicate aircraft resistance coefficient；CLIndicate aircraft lift coefficient；F indicates ground Friction coefficient；W indicates gravity suffered by aircraft；X indicates aircraft horizontal displacement.
The above-mentioned preferred value of each physical quantity is as shown in table 1.
Each physical quantity value of 1 level-one section of taking off of table
Step 3, level-one air-breathing mode section：After level-one section of taking off, under the action of gravity, aerodynamic force and thrust, with Air-breathing mode rises to the height not less than 25km, and the flight time of level-one air-breathing mode section is t2, and t2 is preferably 385s.
The force analysis of level-one air-breathing mode section is as shown in figure 4, the equation of motion of level-one air-breathing mode section indicates as follows：
In formula：ax、ayThe gentle vertical direction acceleration of aircraft water is indicated respectively；θ indicates the aircraft angle of attack.
By ax、ayIt is indicated respectively with acos θ and asin θ, the above formula in formula (2) is multiplied by cos θ is multiplied by sin plus following formula θ, abbreviation can obtain
It above formula in formula (2) is multiplied by sin θ subtracts following formula and be multiplied by cos θ, abbreviation can obtain
Formula (4), which is substituted into formula (3), to be obtained
In formula：(g0, R, H indicate respectively earth surface acceleration of gravity, earth radius and The residing height of aircraft)；
Can obtain the aircraft air-breathing mode section differential equation of motion that climbs by formula (5) is
In formula, T indicates the motor power suffered by aircraft when in level-one air-breathing mode section；m1It indicates to inhale in level-one The initial gross mass of aircraft when gas schema section；Indicate aircraft fuel wear rate；g0Indicate that earth surface gravity accelerates Degree；K indicates lift resistance ratio coefficient；L indicates aerodynamic lift suffered by aircraft；D indicates aerodynamic drag suffered by aircraft；CLIndicate flight Device lift coefficient；CDIndicate aircraft resistance coefficient.
H (H≤25km) is small value relative to earth radius R in formula (5), is approximately consideredTherefore obtain level-one One simplified equation of motion of air-breathing mode section is：
When in level-one air-breathing mode section, as shown in Figure 1, the thrust of SABRE engines rises with height and is increased.
Step 4, one-stage rocket schema section：After level-one air-breathing mode section, SABRE engines are switched to rocket mode simultaneously Two-stage spacecraft of entering the orbit is pushed to continue to climb, after the height for reaching 100km, the first order and second level separation, the first order is unpowered The mode of gliding, which returns to ground, to be realized and reuses, and level-one as shown in Figure 10 is given an encore section.
The flight time of one-stage rocket schema section is t3, and t3 is preferably 304s.
In one-stage rocket schema section, aircraft is climbed with fixed elevation, and force analysis is identical as level-one air-breathing mode section, fortune Shown in dynamic equation such as formula (6).
When in one-stage rocket schema section, the thrust of SABRE engines remains unchanged, preferably 1458kN.
Step 5, two level is climbed section：After the first order and second level separation, the second level is climbed vertically, and is carried out in Trajectory-terminal Gravity is turned, and with the speed more than 7700m/s, and preferably with the speed of 7925.009m/s, payload is sent into 300km's LEO.
Two level climb section flight time be t4, t4 is preferably 33s namely t2 ＞ t3 ＞ t1 ＞ t4, total flight time 768s
When two level is climbed section, due to being located at 100km height or more, atmospheric density is very thin, and aircraft climbs vertically, no Consider further that effect of the aerodynamic force to aircraft, force analysis are as shown in Figure 5.
Two level climb section the equation of motion indicate it is as follows：
In formula：Motor power suffered by aircraft when T indicates to climb section in two level；W indicates gravity suffered by aircraft；m2 Indicate the initial gross mass of aircraft when rocket mode rises at 100km；Indicate fuel consumption flow；Isp expressions liquid oxygen/ Hydrogen rocket specific impulse.
The mixing ratio of liquid oxygen/liquid hydrogen takes 6.04 in calculating process, starts according to suffered by aircraft when climbing section in two level Machine thrust can quickly calculate the weight needed for required liquid oxygen or liquid hydrogen.
In step 5, the second level is climbed vertically, and carries out gravity turning in Trajectory-terminal, and with speed by payload It is sent into the LEO of 300km.
The equation of motion in aforementioned four stage is solved using fourth-order Runge-Kutta method, as a result as shown in figs. 6-9.
From fig. 6 it can be seen that first order ramp-up period, aircraft acceleration is smaller, peak acceleration 21.18m/ S2, this is to overcome air drag work done to reduce.Second level ramp-up period, aircraft leave dense atmosphere, accelerate Degree increases rapidly, in order to reach speed of entering the orbit.
From figure 7 it can be seen that first order maximum speed is 4882.076m/s, second level maximum speed is 7909.964m/ s。
As can be seen from Figure 8 at the first order and second level burble point, apart from takeoff point 1147.446km, it is seen that be more Utilization aerodynamic lift, aircraft carried out longer-distance flight in dense atmosphere.
From fig. 9, it can be seen that the first order is detached with the second level at 100.01km, the second level is climbed rapidly after separation, most The height of 300km is reached eventually.
According to simulation result, total flight time 768s, the time used in each mission phase is as shown in table 2.
2 each mission phase of table corresponds to the period
According to simulation result, it is known that when aircraft reaches the LEO of 300km, speed 7925.009m/s, Meet speed requirement of entering the orbit (speed of entering the orbit be 7700m/s), it is believed that payload can be sent into LEO, of the invention two Grade enter the orbit spacecraft method of entering the orbit it is feasible.
The preferred embodiment of the present invention has been described above in detail, still, during present invention is not limited to the embodiments described above Detail can carry out a variety of equivalents to technical scheme of the present invention within the scope of the technical concept of the present invention, this A little equivalents all belong to the scope of protection of the present invention.

Claims (10)

  1. The method of entering the orbit of spacecraft 1. the two-stage that a kind of first order can be reused is entered the orbit, it is characterised in that：Include the following steps：
    Step 1, two-stage is entered the orbit the model construction of spacecraft：Two-stage spacecraft of entering the orbit includes the first order and the second level；First order structure Type is sky tower, using SABRE engines as power plant；The second level is pencil rocket, using liquid hydrogen/oxygen rocket motor Machine is as power plant；Payload in the second level accounts for the 5.89% of gross mass of taking off；
    Step 2, level-one section of taking off：Two-stage enters the orbit spacecraft near terrestrial equator, leaves ground with fixed elevation θ, level-one rises The flight time for flying section is t1；
    Step 3, level-one air-breathing mode section：After level-one section of taking off, under the action of gravity, aerodynamic force and thrust, with air-breathing Pattern rises to the height not less than 25km, and the flight time of level-one air-breathing mode section is t2；
    Step 4, one-stage rocket schema section：After level-one air-breathing mode section, SABRE engines are switched to rocket mode and push Two-stage spacecraft of entering the orbit continues to climb, after the height for reaching 100km, the first order and second level separation, and gliding that the first order is unpowered Mode return ground realize reuse；The flight time of one-stage rocket schema section is t3；
    Step 5, two level is climbed section：After the first order and second level separation, the second level is climbed vertically, and carries out gravity in Trajectory-terminal It turns, and payload is sent into the LEO of 300km with the speed more than 7700m/s；Two level is climbed flight time of section For t4.
  2. 2. the two-stage that the first order according to claim 1 can be reused is entered the orbit, the method for entering the orbit of spacecraft, feature exist In：In step 1, the structural coefficient of the first order is 0.1902, and the structural coefficient of the second level is 0.12.
  3. 3. the two-stage that the first order according to claim 1 can be reused is entered the orbit, the method for entering the orbit of spacecraft, feature exist In：In step 3, when being in level-one air-breathing mode section, the thrust of SABRE engines rises with height and is increased；In step 4, place When one-stage rocket schema section, the thrust of SABRE engines remains unchanged.
  4. 4. the two-stage that the first order according to claim 1 can be reused is entered the orbit, the method for entering the orbit of spacecraft, feature exist In：In step 2, the equation of motion of level-one section of taking off is expressed as follows：
    In formula：V indicates aircraft speed；T indicates motor power suffered by aircraft when in level-one section of taking off；D indicates flight Aerodynamic drag suffered by device；F indicates ground friction resistance suffered by aircraft；L indicates aerodynamic lift suffered by aircraft；M indicates flight Device quality；m0Indicate mass of loaded vehicle；Indicate aircraft fuel wear rate；ρ indicates aircraft present position air Density；S indicates aircraft feature area；CDIndicate aircraft resistance coefficient；CLIndicate aircraft lift coefficient；F indicates that ground is rubbed Wipe coefficient；W indicates gravity suffered by aircraft；X indicates aircraft horizontal displacement.
  5. 5. the two-stage that the first order according to claim 1 can be reused is entered the orbit, the method for entering the orbit of spacecraft, feature exist In：In step 3, the equation of motion of level-one air-breathing mode section indicates as follows：
    Wherein,
    In formula, T indicates the motor power suffered by aircraft when in level-one air-breathing mode section；m1It indicates to be in level-one air-breathing mould The initial gross mass of aircraft when formula sectionIndicate aircraft fuel wear rate；g0Indicate earth surface acceleration of gravity；K tables Show lift resistance ratio coefficient；L indicates aerodynamic lift suffered by aircraft；D indicates aerodynamic drag suffered by aircraft；CLIndicate aircraft lift Coefficient；CDIndicate aircraft resistance coefficient.
  6. 6. the two-stage that the first order according to claim 1 can be reused is entered the orbit, the method for entering the orbit of spacecraft, feature exist In：In step 4, the equation of motion of one-stage rocket schema section indicates as follows：
    Wherein,
    In formula, T indicates the motor power suffered by aircraft when in one-stage rocket schema section；m1It indicates to be in one-stage rocket mould The initial gross mass of aircraft when formula section；Indicate aircraft fuel wear rate；g0, R, H indicate earth surface gravity respectively The residing height of acceleration, earth radius and aircraft；K indicates lift resistance ratio coefficient；L indicates flight vehicle aerodynamic lift；D indicates flight Aerodynamic drag suffered by device；CLIndicate aircraft lift coefficient；CDIndicate aircraft resistance coefficient；θ indicates the aircraft angle of attack.
  7. 7. the two-stage that the first order according to claim 1 can be reused is entered the orbit, the method for entering the orbit of spacecraft, feature exist In：In step 5, two level climb section the equation of motion indicate it is as follows：
    In formula：Motor power suffered by aircraft when T indicates to climb section in two level；W indicates gravity suffered by aircraft；m2It indicates The initial gross mass of aircraft when rocket mode rises at 100km；Indicate fuel consumption flow；Isp indicates liquid oxygen/liquid hydrogen Rocket engine specific impulse.
  8. 8. the two-stage that the first order according to claim 1 can be reused is entered the orbit, the method for entering the orbit of spacecraft, feature exist In：T1=46s, t2=385s, t3=304s, t4=33s, total flight time 768s.
  9. 9. the two-stage that the first order according to claim 1 can be reused is entered the orbit, the method for entering the orbit of spacecraft, feature exist In：In step 5, the second level is climbed vertically, and carries out gravity turning in Trajectory-terminal, and will be had with the speed of 7925.009m/s Imitate the LEO that load is sent into 300km.
  10. 10. the two-stage that the first order according to claim 1 can be reused is entered the orbit, the method for entering the orbit of spacecraft, feature exist In：In step 1, the second level as power plant, is highly higher than residing for the rocket engine using liquid hydrogen/oxygen rocket engine After the design height of jet pipe, specific impulse will stay in that vacuum specific impulse and numerical value no longer changes；The vacuum specific impulse of hydrogen-oxygen rocket is 4500m/s controls rocket engine thrust in flight course by adjusting fuel flow rate.
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Application publication date: 20180821