CN111038699B - Separable composite range extending system and method on aircraft - Google Patents
Separable composite range extending system and method on aircraft Download PDFInfo
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- CN111038699B CN111038699B CN201811187339.1A CN201811187339A CN111038699B CN 111038699 B CN111038699 B CN 111038699B CN 201811187339 A CN201811187339 A CN 201811187339A CN 111038699 B CN111038699 B CN 111038699B
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- 238000000034 method Methods 0.000 title claims abstract description 23
- 239000002131 composite material Substances 0.000 title claims abstract description 20
- 239000000446 fuel Substances 0.000 claims abstract description 21
- 239000002760 rocket fuel Substances 0.000 claims abstract description 14
- JTJMJGYZQZDUJJ-UHFFFAOYSA-N phencyclidine Chemical compound C1CCCCN1C1(C=2C=CC=CC=2)CCCCC1 JTJMJGYZQZDUJJ-UHFFFAOYSA-N 0.000 claims abstract description 13
- 238000005096 rolling process Methods 0.000 claims abstract description 10
- 238000002485 combustion reaction Methods 0.000 claims description 18
- 150000001875 compounds Chemical class 0.000 claims description 13
- 238000002347 injection Methods 0.000 claims description 11
- 239000007924 injection Substances 0.000 claims description 11
- 230000009471 action Effects 0.000 claims description 4
- 238000013459 approach Methods 0.000 claims description 3
- 230000001174 ascending effect Effects 0.000 claims description 3
- 238000005507 spraying Methods 0.000 claims description 3
- 238000000926 separation method Methods 0.000 description 12
- 239000004606 Fillers/Extenders Substances 0.000 description 7
- 239000002828 fuel tank Substances 0.000 description 6
- 230000008569 process Effects 0.000 description 6
- 230000001133 acceleration Effects 0.000 description 5
- 238000006243 chemical reaction Methods 0.000 description 3
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- 238000004880 explosion Methods 0.000 description 3
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- 238000002474 experimental method Methods 0.000 description 2
- 238000012986 modification Methods 0.000 description 2
- 230000004048 modification Effects 0.000 description 2
- 238000004088 simulation Methods 0.000 description 2
- 238000006467 substitution reaction Methods 0.000 description 2
- 230000007246 mechanism Effects 0.000 description 1
- 238000002360 preparation method Methods 0.000 description 1
- 230000002035 prolonged effect Effects 0.000 description 1
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENT OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
- B64D1/00—Dropping, ejecting, releasing, or receiving articles, liquids, or the like, in flight
- B64D1/02—Dropping, ejecting, or releasing articles
- B64D1/04—Dropping, ejecting, or releasing articles the articles being explosive, e.g. bombs
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENT OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
- B64D1/00—Dropping, ejecting, releasing, or receiving articles, liquids, or the like, in flight
- B64D1/02—Dropping, ejecting, or releasing articles
- B64D1/04—Dropping, ejecting, or releasing articles the articles being explosive, e.g. bombs
- B64D1/06—Bomb releasing; Bomb doors
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02K—JET-PROPULSION PLANTS
- F02K9/00—Rocket-engine plants, i.e. plants carrying both fuel and oxidant therefor; Control thereof
- F02K9/95—Rocket-engine plants, i.e. plants carrying both fuel and oxidant therefor; Control thereof characterised by starting or ignition means or arrangements
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- G—PHYSICS
- G05—CONTROLLING; REGULATING
- G05D—SYSTEMS FOR CONTROLLING OR REGULATING NON-ELECTRIC VARIABLES
- G05D1/00—Control of position, course, altitude or attitude of land, water, air or space vehicles, e.g. using automatic pilots
- G05D1/10—Simultaneous control of position or course in three dimensions
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Abstract
The invention discloses a separable composite range extending system and a separable composite range extending method on an aircraft, wherein a rocket range extending module, a bottom row range extending module, a rolling range extending module and a gliding range extending module are simultaneously arranged in the system, all the modules work cooperatively and alternately in different flight stages according to a preset sequence without mutual interference, and the range of the aircraft can be improved, so that the final range of the aircraft is improved to the maximum extent; in addition, the rocket range extending module needs a large-size storage space for filling fuel, and the rocket fuel tank can increase more burden on the subsequent flight of the aircraft, so that after the work of the rocket engine is finished, the rocket fuel tank and the tail part of the aircraft where the rocket fuel tank is located are separated from the aircraft body, and the range of the aircraft is further improved.
Description
Technical Field
The invention relates to the field of aircraft control, in particular to a separable composite range extending system and method on an aircraft.
Background
Modern battlefields put higher requirements on the range of the guided aircraft, and the increase of the range can improve the survival probability of fighters and generate richer strategies and tactics. However, in the prior art, although there are some methods for increasing the range of the aircraft, such as boosting by a rocket engine, further increasing the altitude and the speed, such as reducing the drag by increasing the air temperature at the tail of the aircraft by a bottom-row method, these methods are not coordinated and unified, and are not concentrated in the same aircraft; in other schemes, the glide angle of the glide section is adjusted, but the excessive adjustment of the glide angle can reduce the speed value when the aircraft hits a target, namely, the landing speed is reduced, so the range-extending scheme has to be abandoned in many times; in addition, the range-extending effect in the prior art still cannot meet the increasing requirement of a long range, and more and better range-extending schemes need to be designed.
For the above reasons, the present inventors have made extensive studies on the existing range extending system and method of an aircraft, and have awaited designing a range extending system and method capable of solving the above problems, and maximizing the range of the aircraft.
Disclosure of Invention
In order to overcome the problems, the inventor of the invention carries out intensive research and designs a separable composite range extending system and a separable composite range extending method on an aircraft, wherein the system is simultaneously provided with a rocket range extending module, a bottom row range extending module, a rolling range extending module and a gliding range extending module, all the modules work in a cooperative mode and alternately work in different flight stages according to a preset sequence without mutual interference, and the range of the aircraft can be improved, so that the final range of the aircraft is improved to the maximum extent; in addition, the rocket range extending module needs a storage space with a larger volume to be filled with fuel, and the rocket fuel tank can increase more burden on the subsequent flight of the aircraft, so that after the work of the rocket engine is finished, the rocket fuel tank and the tail part of the aircraft where the rocket fuel tank is located are separated from the aircraft body, the range of the aircraft is further improved, and the invention is completed.
In particular, it is an object of the present invention to provide a detachable composite range extender system for an aircraft that includes a plurality of range extender modules that cooperate to increase the range of the aircraft.
Wherein the composite range extending system comprises a rocket range extending module,
the rocket range extending module comprises a rocket engine 1 arranged at the tail part of an aircraft,
the rocket engine 1 starts to work in the ascending stage of the aircraft and is used for improving the speed and the maximum altitude of the aircraft;
preferably, the working time of the rocket engine 1 is 5-10 seconds.
Wherein a rocket fuel tank 2 connected with the rocket engine 1 is arranged at the tail part of the aircraft;
preferably, the aircraft tail is detachable from the aircraft body;
more preferably, the aircraft tail is detached from the aircraft body when the aircraft is near the zenith.
Wherein the composite range extending system comprises a bottom discharge range extending module,
the bottom exhaust range extending module comprises an exhaust device 3 arranged on the side of the tail part of the aircraft and a combustion chamber 4 connected with the exhaust device,
high-temperature gas generated after the fuel in the combustion chamber 4 is combusted is discharged from the exhaust device, the temperature of air at the bottom of the aircraft is increased, and an air flow field is changed, so that the resistance at the bottom of the aircraft is reduced, and the range of the aircraft is increased.
Wherein the bottom row range extending module continues to work until the fuel in the combustion chamber 4 is exhausted before the aircraft reaches the highest point;
preferably, the combustion time of the fuel in the combustion chamber 4 is 15-25 seconds.
Wherein the composite range extending system comprises a rolling range extending module,
the rolling range-extending module comprises a pulse air injection device 5 which is arranged at the side part of the aircraft body and is arranged at an interval with the empennage,
the pulse jet device 5 reduces the swing amplitude of the aircraft and improves the flight range of the aircraft under the action of jet thrust.
After the pulse jet device 5 is started to work, gas is jetted to the left side of the tail wing at intervals of specific time in a direction perpendicular to the main body of the aircraft, so that the rotating speed of the aircraft is increased, and the swing amplitude of the aircraft is reduced;
preferably, the tail fin is provided with 8 pieces, and correspondingly, the air injection device is also provided with 8 pieces.
Wherein the compound range-extending system comprises a gliding range-extending module,
the glide range-extending module comprises a glide inclination angle adjusting module, the glide inclination angle adjusting module is used for controlling the inclination angle of the aircraft in the glide section,
preferably, the glide slope angle adjusting module controls the slope angle of the aircraft to be below 20 degrees in the glide section.
Wherein, the glide range-increasing module also comprises a terminal guidance speed-increasing nozzle 7 arranged at the bottom of the aircraft main body,
the terminal guidance speed-increasing nozzle 7 starts to work after the aircraft enters a terminal guidance stage for a preset time, and the falling speed of the aircraft is increased by spraying high-temperature and high-pressure gas from the terminal guidance speed-increasing nozzle 7, so that the aircraft still has the falling speed of more than 300 m/s when the glide angle meets the condition of less than 20 ℃;
preferably, the last guidance speed-increasing nozzle 7 starts to work after the aircraft enters the last guidance stage for 3 seconds, and the working time is 2-3 seconds.
The invention also provides a composite range extending method on an aircraft,
in the method, after the aircraft is launched, the bottom row range extending module is firstly started to work,
after the empennage is popped up, the rotating speed of the engine body is reduced, and the posture is gradually stabilized, the rocket range extending module starts to work, and the rocket range extending module and the bottom row range extending module work synchronously at the moment;
when the aircraft approaches the top point of the flight trajectory, the tail of the aircraft is separated from the aircraft body;
after the tail part of the aircraft is separated from the aircraft body, the rolling range-extending module starts to work, and the swing amplitude of the aircraft is reduced through the pulse air injection device;
the glide range-increasing module starts to work after the starting control of the aircraft, the glide inclination angle adjusting module controls the aircraft to glide at an inclination angle smaller than 20 degrees, the aircraft enters a terminal guidance stage for 3 seconds, the terminal guidance speed-increasing nozzle starts to work, fuel in the nozzle is combusted and then is sprayed out, the falling speed of the aircraft is improved, and the aircraft can reach a target point at a preset falling speed.
The invention has the advantages that:
(1) the separable composite range extending system on the aircraft is provided with at least four range extending modules, so that the flight speed, the resistance and the energy loss can be increased at each flight stage of the aircraft, and the range of the aircraft is increased finally;
(2) in the separable composite range extending system on the aircraft, the tail part of the aircraft provided with the rocket range extending module and the bottom row range extending module can be separated from the main body of the aircraft after the work is finished, so that the burden of the aircraft is reduced, and the range of the aircraft is further improved.
Drawings
FIG. 1 illustrates a schematic diagram of an overall configuration of a detachable compound range extender system on an aircraft in accordance with a preferred embodiment of the present invention;
FIG. 2 illustrates a corresponding aircraft trajectory diagram during operation of a detachable composite range extender system on an aircraft in accordance with a preferred embodiment of the present invention;
fig. 3 shows flight trajectories of various aircraft in the experimental example.
The reference numbers illustrate:
1-rocket engine
2-rocket fuel tank
3-exhaust device
4-combustion chamber
5-pulse air injection device
6-pulse fuel tank
7-terminal guidance speed-increasing nozzle
8-terminal guidance speed-increasing fuel tank
Detailed Description
The invention is explained in more detail below with reference to the figures and examples. The features and advantages of the present invention will become more apparent from the description.
The word "exemplary" is used exclusively herein to mean "serving as an example, embodiment, or illustration. Any embodiment described herein as "exemplary" is not necessarily to be construed as preferred or advantageous over other embodiments. While the various aspects of the embodiments are presented in drawings, the drawings are not necessarily drawn to scale unless specifically indicated.
The process that the aircraft is launched from the launching point to finally hit the target generally comprises the following processes, as shown in fig. 2, after the aircraft flies out from the launching device, the empennage is firstly popped out, in the process that the aircraft ascends and quickly arrives at the top point, the process is started, the gyro is unlocked, preparation is made for starting control, after the starting control, the aircraft enters the gliding stage through the highest point, slides to the target in a curve as smooth as possible, and enters the final guide section when approaching the target, and the attitude and the direction of the aircraft are adjusted through the steering engine, so that the target can be finally hit.
In accordance with the present invention, there is provided an on-board detachable composite range extender system, as shown in fig. 1 and 2, which includes a plurality of range extender modules that are cooperatively operable to increase the range of an aircraft. The multiple range extending modules comprise a rocket range extending module, a bottom discharge range extending module, a rolling range extending module and a gliding range extending module; the aircraft is powered or energy loss is reduced at various stages of flight of the aircraft so as to achieve the purpose of range extension.
In a preferred embodiment, as shown in fig. 1, 2, the rocket range module comprises a rocket engine 1 arranged aft of the aircraft,
the rocket engine 1 starts to work in the ascending stage of the aircraft and is used for improving the speed and the maximum altitude of the aircraft;
preferably, the working time of the rocket engine 1 is 5-10 seconds, and in the period of time, the energy with the total rush time of 100000-130000 (Newton's) can be provided for the aircraft, so that the speed of the aircraft is increased from 200-400 m/s to 900-1300 m/s.
More preferably, a rocket fuel tank 2 connected to the rocket engine 1 is provided at the tail of the aircraft; the working process is as follows: the rocket engine burns the fuel stored in the rocket fuel tank 2 and quickly discharges the high-temperature gas obtained by burning from the tail of the aircraft, so that the rocket engine has great reaction force and provides assistance for accelerating the aircraft;
preferably, the aircraft tail can be separated from the aircraft body, the separation can also be called as missile-rocket separation, the volume and the weight of the aircraft body can be reduced through the separation, the subsequent energy loss can be reduced, the flight distance of the aircraft is prolonged, and the range is increased;
more preferably, the tail of the aircraft is separated from the aircraft body when the aircraft is near the highest point, at this time, the bottom-row range extending module mounted at the tail of the aircraft also finishes the work content, the carried fuel is used up, and the power assisting for the range extending is not provided any more, so that the rocket range extending module and the bottom-row range extending module are separated from each other at the same time through separation at the moment, the bottom of the aircraft body is exposed outside, and a sufficient working space is reserved for the subsequent further range extending operation.
According to the separation method, the tail part of the aircraft is connected with the aircraft body through the explosion bolt, the timing of separating the projectile and the rocket can be determined according to the speed of the aircraft or the flight time of the aircraft, a built-in clock starts to time after the aircraft is launched, when the time reaches the separation time or the speed of the aircraft reaches the separation speed, a built-in battery starts to supply power, the explosion bolt is detonated, and therefore the tail part of the aircraft is separated from the aircraft body, the separation time is usually 3-5 seconds, the separation speed is 500-1100 m/s, namely when any one of the separation time or the separation speed reaches a preset value, the projectile and rocket separation operation is executed; the connecting/separating structure of the explosion bolt and the like is a commonly used structure in the field, and particularly refers to the improved design of a low-overload rocket projectile and rocket separating mechanism, namely Zhang Shilin, Wanggang' bullets and arrows and guidance bulletin 2017;
in a preferred embodiment, as shown in fig. 1 and 2, the bottom row range extending module comprises an exhaust device 3 arranged at the side of the tail part of the aircraft and a combustion chamber 4 connected with the exhaust device,
high-temperature gas generated after the fuel in the combustion chamber 4 is combusted is discharged from the exhaust device, the temperature of air at the bottom of the aircraft is increased, and an air flow field is changed, so that the resistance at the bottom of the aircraft is reduced, and the range of the aircraft is increased. The high-temperature gas is discharged from the exhaust device at a relatively slow speed, which is different from the operating purpose of a rocket engine, and the high-temperature gas is accelerated without the aid of the reaction force of jet and only the temperature of the bottom of the aircraft is increased.
Because the exhaust device is positioned at the side of the tail part of the aircraft and does not interfere with the rocket engine 1 arranged on the tail part of the aircraft, the exhaust device can coexist in a synergic manner and even can work simultaneously.
Preferably, the bottom row range extending module continues to operate until the fuel in the combustion chamber 4 is exhausted before the aircraft reaches the peak; the bottom row range extending module can start to work after the tail wing is popped up, the specific working time depends on the loading amount, and the bottom row range extending module can work all the time before the fuel is exhausted.
Preferably, the combustion time of the fuel in the combustion chamber 4 is 15-25 seconds, namely the carried fuel can allow the bottom discharge range-extending module to work for 15-25 seconds, and more preferably 20-25 seconds.
In a preferred embodiment, as shown in fig. 1 and 2, the roll range module comprises an impulse jet device 5 arranged at the side of the aircraft body and spaced from the tail wing,
the pulse jet device 5 reduces the swing amplitude of the aircraft and the capacity loss of the aircraft in the flying process under the action of jet thrust, thereby improving the flight range of the aircraft. The pulse jet device 5 is connected with a pulse fuel tank 6, and the pulse fuel tank 6 supplies fuel to the pulse jet device 5; the pulse jet device 5 is started to work after the tail part of the aircraft is separated from the main body of the aircraft, and mainly works in a gliding section; the working time of the pulse jet device 5 is 70-100 seconds, the working time depends on the duration of the gliding section, and the corresponding working time needs to be selected according to the duration of the gliding section
After the pulse jet device 5 is started to work, the pulse jet device 5 jets air to the left side of the tail wing at intervals of specific time in a direction perpendicular to the main body of the aircraft, wherein the specific time is preferably 3 seconds, so that the rotating speed of the aircraft is increased, and the swinging amplitude of the aircraft is reduced;
preferably, the tail fin is provided with 8 pieces, and correspondingly, the air injection device is also provided with 8 pieces. For 4 fin tail wing aircraft of tradition, through setting up 8 fins in this application, improve the stability of aircraft, reduce the range of swaying of aircraft, reduce the energy loss of flight in-process, set up air jet system on this basis, can further reduce energy loss, improve the aircraft range.
The pulse air injection devices work synchronously, so that the whole stress is uniform.
In a preferred embodiment, as shown in fig. 1, 2, the glide range module includes a glide pitch module for controlling the pitch of the aircraft during the glide phase,
preferably, the glide inclination angle adjusting module controls the inclination angle of the aircraft to be less than 20 degrees in the glide section, and preferably 15-20 degrees. In the prior art, the glide inclination angle of an aircraft in the glide phase is generally maintained within the range of 30-50 degrees, so that sufficient landing speed is obtained, and the glide distance is naturally short;
specifically, the glide inclination angle adjusting module adjusts the direction and the posture of the aircraft by controlling a steering engine to steer, and enables the aircraft to glide at the specific speed and the specific inclination angle; namely, the inclination angle is less than 20 degrees, preferably, the inclination angle is 15-20 degrees;
the glide inclination angle adjusting module can adopt a singlechip of DSP28335 of TI company;
preferably, the glide range-increasing module further comprises a terminal guidance speed-increasing nozzle 7 arranged at the bottom of the aircraft body;
the terminal guidance speed-increasing nozzle 7 starts to work after the aircraft enters a terminal guidance stage for a preset time, and the falling speed of the aircraft is increased by spraying high-temperature and high-pressure gas from the terminal guidance speed-increasing nozzle 7, so that the aircraft still has the falling speed of more than 300 m/s when the glide angle meets the condition of less than 20 ℃; in the prior art, the glide inclination angle is controlled within the range of 30-50 degrees, so that the landing speed of the aircraft can reach 200-240 m/s, the most basic use requirement can be basically met, and the action effect of the aircraft can be naturally further improved if the landing speed can be improved.
Terminal guidance acceleration rate spout 7 links to each other with terminal guidance acceleration rate fuel tank 8, and terminal guidance acceleration rate fuel tank 8 provides fuel for terminal guidance acceleration rate spout 7, and the high temperature high pressure gas that fuel burning produced spouts from terminal guidance acceleration rate spout 7, under the effect of reaction force, provides forward power for the aircraft main part, improves the speed of aircraft main part, increases the falling speed of aircraft promptly.
Preferably, the last guidance speed-increasing nozzle 7 starts to work after the aircraft enters the last guidance stage for 3 seconds, and the working time is 2-3 seconds. In the period of time, the energy with the total rush time of 18000-32000 (Newton) seconds can be provided for the aircraft, and the speed of the aircraft is improved from 100-150 m/s to 300-500 m/s.
The invention also provides a composite range extending method on an aircraft,
the method comprises the following steps of,
after the aircraft is launched, the bottom row range extending module is started to work at first to heat the air at the tail part of the aircraft and reduce the air resistance,
after the empennage is popped up, the rotating speed of the engine body is reduced, and the posture is gradually stabilized, the rocket range extending module starts to work, and the rocket range extending module and the bottom row range extending module work synchronously at the moment, so that the speed of the aircraft is quickly increased, and the aircraft can reach a higher height position;
when the aircraft approaches the top point of the flight trajectory, the tail of the aircraft is separated from the aircraft body;
after the tail part of the aircraft is separated from the aircraft body, the rolling range-extending module starts to work, and the swing amplitude of the aircraft is reduced through the pulse air injection device;
the gliding range-increasing module starts to work after the starting control of the aircraft, the gliding inclination angle adjusting module controls the aircraft to glide at an inclination angle of 15-20 degrees, the terminal guidance speed-increasing nozzle starts to work after the aircraft enters a terminal guidance stage for 3 seconds, and fuel in the terminal guidance speed-increasing nozzle is combusted and then is sprayed out, so that the falling speed of the aircraft is improved, and the aircraft can reach a target point at a preset falling speed.
Experimental example:
the flight trajectory of the aircraft is simulated through an aircraft simulation system, five aircraft with the same model are launched in the same launching place and the same direction in a simulation experiment, each aircraft selects a target as far as possible to judge the farthest target which can be hit by the aircraft under the condition of meeting the falling speed constraint, wherein the falling speed constraint is more than 300 m/s in the experiment.
The separable composite range extending system on the aircraft is filled in a first aircraft, as shown in fig. 1, a rocket range extending module, a bottom-row range extending module, a rolling range extending module and a gliding range extending module are arranged on the aircraft, and the range extending modules work in a coordinated mode to improve the range of the aircraft to the maximum extent; the flight trajectory of the aircraft is shown in a first scheme in fig. 3, and under the condition that the landing speed is more than 300 m/s, the aircraft can hit targets beyond 113 kilometers, and the circular probability error is ensured to be within 15 meters;
only the rocket range extending module is arranged in the second aircraft, namely a rocket engine and a rocket fuel tank are arranged, and the tail part of the second aircraft cannot be separated from the aircraft body; the flight trajectory of the aircraft is shown as a second scheme in fig. 3, and under the condition that the landing speed is more than 300 m/s, the aircraft can hit targets beyond 42 km distance, and the circular probability error is ensured to be within 15 m;
only the rocket range-extending module and the bottom-row range-extending module are arranged in the third aircraft, namely, a rocket engine, a rocket fuel tank, an exhaust device and a combustion chamber are arranged, and the tail part of the aircraft cannot be separated from the aircraft body; the flight trajectory of the aircraft is shown in a third scheme in fig. 3, and under the condition that the landing speed is more than 300 m/s, the aircraft can hit targets beyond 53 km, and the circular probability error is ensured to be within 15 m;
the fourth aircraft is only provided with the rocket range-extending module and the bottom-row range-extending module, namely a rocket engine, a rocket fuel tank, an exhaust device and a combustion chamber, and the tail part of the aircraft can be separated from the aircraft body and is separated from the aircraft body when the aircraft reaches the attachment at the highest point; the flight trajectory of the aircraft is shown as a fourth scheme in fig. 3, and under the condition that the landing speed is more than 300 m/s, the aircraft can hit targets beyond 62 km distance, and the circular probability error is ensured to be within 15 m;
no range extender module is installed in the fifth aircraft; the flight trajectory of the aircraft is shown as a fifth scheme in fig. 3, and under the condition that the landing speed is more than 300 m/s, the aircraft can hit targets beyond 29 km, and the circular probability error is ensured to be within 15 m;
can know through above-mentioned experiment contrast, separable compound journey system that increases on the aircraft that this application provided can improve the aircraft range effectively.
The present invention has been described above in connection with preferred embodiments, but these embodiments are merely exemplary and merely illustrative. On the basis of the above, the invention can be subjected to various substitutions and modifications, and the substitutions and the modifications are all within the protection scope of the invention.
Claims (8)
1. A separable composite range extending system on an aircraft, which is characterized by comprising a plurality of range extending modules capable of working cooperatively, so that the range of the aircraft is increased;
the compound range extending system comprises a roll range extending module,
the rolling range-extending module comprises a pulse air injection device (5) which is arranged at the side part of the aircraft body and is arranged at an interval with the empennage,
the pulse air injection device (5) reduces the swing amplitude of the aircraft and improves the range of the aircraft under the action of air injection thrust;
after the pulse jet device (5) is started to work, gas is jetted to the left side of the tail wing at intervals of specific time in a direction perpendicular to the main body of the aircraft, so that the rotating speed of the aircraft is increased, and the swing amplitude of the aircraft is reduced;
the fin is provided with 8, and corresponding to it, jet system also is provided with 8.
2. The compound range extending system of claim 1,
the compound range extending system comprises a rocket range extending module,
the rocket range extending module comprises a rocket engine (1) arranged at the tail part of an aircraft,
the rocket engine (1) starts to work in the ascending stage of the aircraft and is used for improving the speed and the maximum altitude of the aircraft;
the working time of the rocket engine (1) is 5-10 seconds.
3. The compound range extending system of claim 2,
a rocket fuel tank (2) connected with the rocket engine (1) is arranged at the tail part of the aircraft;
the aircraft tail can be separated from the aircraft body;
the aircraft tail is separated from the aircraft body when the aircraft is near the peak.
4. The compound range extending system of claim 1,
the compound range extending system comprises a bottom row range extending module,
the bottom exhaust range extending module comprises an exhaust device (3) arranged on the side of the tail part of the aircraft and a combustion chamber (4) connected with the exhaust device,
high-temperature gas generated after fuel in the combustion chamber (4) is combusted is discharged from the exhaust device, the temperature of air at the bottom of the aircraft is increased, and an air flow field is changed, so that the resistance at the bottom of the aircraft is reduced, and the range of the aircraft is increased.
5. The compound range extending system of claim 4,
the bottom row range extending module continuously works until the fuel in the combustion chamber (4) is exhausted before the aircraft reaches the highest point;
the combustion time of the fuel in the combustion chamber (4) is 15-25 seconds.
6. The compound range extending system of claim 1,
the compound range-extending system comprises a gliding range-extending module,
the glide range-extending module comprises a glide inclination angle adjusting module, the glide inclination angle adjusting module is used for controlling the inclination angle of the aircraft in the glide section,
the glide inclination angle adjusting module controls the inclination angle of the aircraft to be below 20 degrees in the glide section.
7. The compound range extending system of claim 6,
the glide range-increasing module also comprises a terminal guidance speed-increasing nozzle (7) arranged at the bottom of the aircraft main body,
the terminal guidance speed-increasing nozzle (7) is started to work after the aircraft enters a terminal guidance stage for a preset time, and the falling speed of the aircraft is increased by spraying high-temperature and high-pressure gas from the terminal guidance speed-increasing nozzle (7), so that the aircraft still has the falling speed of more than 300 m/s when the glide angle meets the condition of less than 20 ℃;
and the last guidance speed-increasing nozzle (7) starts to work after the aircraft enters the last guidance stage for 3 seconds, and the working time is 2-3 seconds.
8. A composite range extending method on an aircraft is characterized in that,
in the method, after the aircraft is launched, the bottom row range extending module is firstly started to work,
after the empennage is popped up, the rotating speed of the engine body is reduced, and the posture is gradually stabilized, the rocket range extending module starts to work, and the rocket range extending module and the bottom row range extending module work synchronously at the moment;
when the aircraft approaches the top point of the flight trajectory, the tail of the aircraft is separated from the aircraft body;
after the tail part of the aircraft is separated from the aircraft body, the rolling range-extending module starts to work, and the swing amplitude of the aircraft is reduced through the pulse air injection device;
the glide range-increasing module starts to work after the starting control of the aircraft, the glide inclination angle adjusting module controls the aircraft to glide at an inclination angle smaller than 20 degrees, the aircraft enters a terminal guidance stage for 3 seconds, the terminal guidance speed-increasing nozzle starts to work, fuel in the nozzle is combusted and then is sprayed out, the falling speed of the aircraft is improved, and the aircraft can reach a target point at a preset falling speed.
Priority Applications (3)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201811187339.1A CN111038699B (en) | 2018-10-12 | 2018-10-12 | Separable composite range extending system and method on aircraft |
| PCT/CN2019/092206 WO2020073683A1 (en) | 2018-10-12 | 2019-06-21 | Separable combined range-extending system and method for aircraft |
| JP2021502937A JP7137255B2 (en) | 2018-10-12 | 2019-06-21 | Composite cruising distance extension system and method that can be separated from flying objects |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
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| CN201811187339.1A CN111038699B (en) | 2018-10-12 | 2018-10-12 | Separable composite range extending system and method on aircraft |
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| Publication Number | Publication Date |
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| CN111038699A CN111038699A (en) | 2020-04-21 |
| CN111038699B true CN111038699B (en) | 2021-03-19 |
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| CN201811187339.1A Active CN111038699B (en) | 2018-10-12 | 2018-10-12 | Separable composite range extending system and method on aircraft |
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| JP (1) | JP7137255B2 (en) |
| CN (1) | CN111038699B (en) |
| WO (1) | WO2020073683A1 (en) |
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| CN112459906B (en) * | 2020-12-04 | 2021-10-15 | 北京理工大学 | Power range-extending gliding aircraft constant-speed cruise adjustment method based on turbojet engine |
| CN114615614B (en) * | 2020-12-09 | 2023-07-25 | 北京理工大学 | Interactive check-up system of many aircraft |
| CN113899254B (en) * | 2021-08-31 | 2024-04-09 | 北京航空航天大学 | Gliding and increasing Cheng Jingque controlled rocket with gliding and increasing range section, full rocket guide rotating wing and control assembly |
| CN116049998B (en) * | 2023-03-30 | 2023-06-30 | 中国人民解放军96901部队 | Method and device for quickly determining separation point parameters of variable-level combined aircraft |
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| GB8915503D0 (en) * | 1989-07-06 | 1994-09-21 | Ml Aviat Ltd | Store ejector |
| JP3336743B2 (en) * | 1994-06-13 | 2002-10-21 | 三菱電機株式会社 | Flight control device |
| US6360993B1 (en) * | 1999-04-09 | 2002-03-26 | Space Systems/ Loral, Inc. | Expendable launch vehicle |
| CN2419572Y (en) * | 2000-04-03 | 2001-02-14 | 中国人民解放军第3305工厂 | Range extanding shell |
| JP2002228400A (en) | 2001-01-26 | 2002-08-14 | Toshiba Corp | Multi-stage rocket motor |
| JP2004211992A (en) | 2003-01-06 | 2004-07-29 | Mitsubishi Electric Corp | Guided missile |
| CN1786450A (en) * | 2004-12-08 | 2006-06-14 | 中国北方工业公司 | Method for preventing mutual interference between bottom row device and rocket engine |
| CN1687694A (en) * | 2005-04-28 | 2005-10-26 | 张永刚 | Projectile of range increased shell |
| JP5127284B2 (en) | 2007-04-11 | 2013-01-23 | 三菱プレシジョン株式会社 | Flying object and apparatus for detecting rotational position of flying object |
| DE102007059397A1 (en) * | 2007-12-10 | 2009-06-18 | Diehl Bgt Defence Gmbh & Co. Kg | swash detonator |
| JP2009257629A (en) | 2008-04-14 | 2009-11-05 | Mitsubishi Electric Corp | Side thruster device |
| US8387360B2 (en) * | 2008-05-21 | 2013-03-05 | Raytheon Company | Integral thrust vector and roll control system |
| JP5626768B2 (en) | 2010-05-28 | 2014-11-19 | 株式会社Ｉｈｉエアロスペース | Flying object |
| CN101892925A (en) * | 2010-06-23 | 2010-11-24 | 中北大学 | Aircraft range-extending technique |
| CN202008324U (en) * | 2011-05-05 | 2011-10-12 | 吉林保利科技中试有限公司 | Base bleed and rocket composite range adding high explosive bomb of 122mm howitzer |
| CN202008325U (en) * | 2011-05-05 | 2011-10-12 | 吉林保利科技中试有限公司 | 130mm howitzer base bleed and rocket compounded extended-range blast fragmentation warhead |
| CN103808212A (en) * | 2013-12-31 | 2014-05-21 | 魏伯卿 | Small missile launched by cannon |
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| CN107401956B (en) * | 2017-08-09 | 2020-07-07 | 南京航空航天大学 | Amphibious cruise missile based on throat offset type pneumatic vectoring nozzle and attitude control method thereof |
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| Publication number | Publication date |
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| JP2022503472A (en) | 2022-01-12 |
| JP7137255B2 (en) | 2022-09-14 |
| WO2020073683A1 (en) | 2020-04-16 |
| CN111038699A (en) | 2020-04-21 |
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