CN214566243U - Two-stage orbital aircraft back quick separation device - Google Patents
Two-stage orbital aircraft back quick separation device Download PDFInfo
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- CN214566243U CN214566243U CN202120320162.9U CN202120320162U CN214566243U CN 214566243 U CN214566243 U CN 214566243U CN 202120320162 U CN202120320162 U CN 202120320162U CN 214566243 U CN214566243 U CN 214566243U
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Abstract
The utility model discloses a two-stage orbit aircraft back quick separation device, the device including form the efflux generator on the carrier for to with the parting surface of the second grade aircraft that the carrier links to each other provides ascending efflux in order to offset the partial gravity of second grade aircraft self. The device can provide ascending efflux to the second grade aircraft and form ascending thrust for the second grade aircraft can rotate relative the carrier and do the new line motion and form first target inclination, increases the angle of pitch of second grade aircraft, makes the produced lift of second grade aircraft increase fast with increasing local angle of attack, makes the second grade aircraft can rise to a take the place to collide with the carrier tail wing fast to a take the place to a take the altitude. The jet generator does not have complex mechanical motion during working, so that the starting speed is high, the jet generator can provide jet for the secondary aircraft after being started, and the time required by the secondary aircraft to reach the safe height can be greatly shortened.
Description
Technical Field
The utility model relates to a two-stage orbit aircraft separation technical field especially relates to a two-stage orbit aircraft back quick separation device.
Background
The two-stage orbit-entering aircraft is a reusable aerospace shuttle tool in the future, and is characterized in that an aircraft carries a two-stage aircraft (a carrier rocket, a space shuttle, an orbiter and the like) to fly to a certain height and separate at a certain speed, then the orbiter is accelerated to climb and enter the orbit, and the aircraft lands horizontally. The two-stage in-orbit aircraft provides a solution with low cost, high reliability and high flexibility for future space launching. In the launching process, the technology of separating the carrier from the secondary aircraft is the key to the success or failure of launching.
In the separation process, strong aerodynamic interference exists between the carrier and the secondary aircraft, the interference is expressed in a shock wave reflection and refraction mode, the interference acts repeatedly in a flow channel formed between the carrier and the secondary aircraft, and the carrier has strong unsteady characteristics and nonlinear characteristics. Meanwhile, the secondary aircraft can only be mounted at the back of the aircraft due to the height of the aircraft landing gear and the internal space. When separating, the secondary aircraft mainly relies on self-lift to separate. However, the separation point is characterized by high speed and low density, although the speed is high (Ma6), the density is low (1.5% of sea level density), and therefore the dynamic pressure is low; the secondary aircraft is generally a space shuttle or a track device, the lift coefficient is small, the shielding effect of the carrier on incoming flow is obvious, the local effective attack angle is small, and the lift of the secondary aircraft is small. In addition, the secondary aircraft is limited by the height of the aircraft landing gear, and the aircraft vertical tail is arranged above the tail, so that the secondary aircraft needs to be quickly lifted to a certain height to avoid collision with the aircraft tail wing in the separation process.
Although the patent document of application No. 201921714836.2 describes a "two-stage in-orbit aircraft back separation device", which can solve the above problems, the jacking mechanism adopted by the device has a complicated structure, a large additional weight and a large amount of energy, and the jacking mechanism generates large pneumatic resistance and pneumatic heating in the separation process, so that the overall design of the aircraft and the flight engineering are difficult to realize. In addition, the jacking separation process is time-consuming and long, and the rapid separation of the carrier and the back of the secondary aircraft cannot be realized.
Disclosure of Invention
The utility model provides a two-stage orbital aircraft back quick separation device.
The utility model provides a following scheme:
a two-stage in-orbit aircraft back quick separation device comprises:
and the jet flow generator is used for providing upward jet flow for a separation surface of a secondary aircraft connected with the carrier so as to offset partial gravity of the secondary aircraft, so that the secondary aircraft and the carrier relatively rotate under an unseparated state to form a first target inclination angle so as to increase the lift force generated by the secondary aircraft.
Preferably: the jet generator is used for providing upward jet to a separation surface of the secondary aircraft, which is positioned in front of the gravity center of the secondary aircraft.
Preferably: the jet flow generator comprises a spray pipe nozzle, and the spray pipe nozzle is positioned on a center of gravity normal projection extension line of the back of the carrier.
Preferably: the jet flow generator comprises a storage box and a combustion chamber, and the spray pipe nozzle is connected with the combustion chamber.
Preferably: a fixed connection mechanism and a hinge mechanism are formed between the separation surfaces of the carrier and the secondary aircraft, and the hinge mechanism is positioned at the tail part of the secondary aircraft; the fixed connection mechanism comprises a first self-release bolt, the first self-release bolt is used for enabling the jet flow and the hinge mechanism to be balanced, the connection between the carrier and the secondary aircraft is released after the gravity of the secondary aircraft, and the secondary aircraft is enabled to rotate relatively by taking the hinge mechanism as a fulcrum under the action of the jet flow to form the first target inclination angle.
Preferably: the hinge mechanism comprises a second self-release bolt, and the second self-release bolt is used for releasing the connection of the hinge mechanism to the carrier and the secondary aircraft after the secondary aircraft and the carrier rotate relatively to form a second target inclination angle under the non-separated state.
Preferably: the first self-releasing bolt and the second self-releasing bolt are explosive bolts.
According to the utility model provides a concrete embodiment, the utility model discloses a following technological effect:
through the utility model discloses, can realize a two-stage orbit aircraft back quick separation device, under an implementation mode, the device can be including forming the efflux generator on the carrier for to with the parting surface of the second grade aircraft that the carrier links to each other provides ascending efflux in order to offset the partial gravity of second grade aircraft self makes the second grade aircraft with the carrier relatively rotates under the non-separation state and forms first target inclination in order to increase the lift that the second grade aircraft produced. The device can provide ascending efflux to the second grade aircraft and form ascending thrust for the second grade aircraft can rotate relative the carrier and do the new line motion and form first target inclination, increases the angle of pitch of second grade aircraft, makes the produced lift of second grade aircraft increase fast with increasing local angle of attack, makes the second grade aircraft can rise to a take the place to collide with the carrier tail wing fast to a take the place to a take the altitude. The jet generator does not have complex mechanical motion during working, so that the starting speed is high, the jet generator can provide jet for the secondary aircraft after being started, and the time required by the secondary aircraft to reach the safe height can be greatly shortened.
Of course, it is not necessary for any particular product to achieve all of the above-described advantages at the same time.
Drawings
In order to more clearly illustrate the embodiments of the present invention or the technical solutions in the prior art, the drawings required to be used in the embodiments will be briefly described below, and it is obvious that the drawings in the following description are only some embodiments of the present invention, and for those skilled in the art, other drawings can be obtained according to these drawings without creative efforts.
Fig. 1 is a schematic structural diagram of a connection state of a two-stage orbital flight vehicle back quick separation device according to an embodiment of the present invention;
fig. 2 is a schematic structural diagram of a two-stage orbital aircraft back quick separation device after separation by a fastening mechanism according to an embodiment of the present invention;
fig. 3 is a schematic structural diagram of a two-stage orbital flight vehicle back quick separation device after separation by a hinge mechanism according to an embodiment of the present invention;
FIG. 4 is a graph illustrating the variation of the displacement of a two-stage aircraft according to an embodiment of the present invention;
fig. 5 is a graph illustrating a change in attitude angle of a second-level aircraft according to an embodiment of the present invention.
In the figure: the aircraft comprises a carrier 1, a jet flow generator 2, a secondary aircraft 3, a fixed connection mechanism 4 and a hinge mechanism 5.
Detailed Description
The technical solutions in the embodiments of the present invention will be described clearly and completely with reference to the accompanying drawings in the embodiments of the present invention, and it is obvious that the described embodiments are only some embodiments of the present invention, not all embodiments. Based on the embodiments in the present invention, all other embodiments obtained by a person skilled in the art all belong to the protection scope of the present invention.
Examples
Referring to fig. 1, fig. 2, fig. 3, fig. 4, and fig. 5, for a two-stage orbital flight vehicle back quick separation device provided by an embodiment of the present invention, as shown in fig. 1, fig. 2, and fig. 3, the device includes a jet generator 2 formed on a carrier 1, for providing an upward jet to a separation surface of a secondary flight vehicle 3 connected to the carrier 1 to offset a partial gravity of the secondary flight vehicle 3 itself, so that the secondary flight vehicle 3 and the carrier 1 relatively rotate to form a first target inclination angle in an unseparated state to increase a lift force generated by the secondary flight vehicle 3.
The secondary aircraft provided by the application can be a carrier rocket, a space shuttle, an orbiter and the like, wherein the separating surface of the secondary aircraft can be the bottom surface of the secondary aircraft, and the separating surface of the carrier can be the top surface of the carrier. This jet generator can provide ascending efflux to the bottom of second grade aircraft and form ascending thrust for the second grade aircraft can rotate relative the carrier and do the motion of raising one's head and form first target inclination, increases the angle of pitch of second grade aircraft, makes the produced lift of second grade aircraft increase fast with increasing local angle of attack, makes the second grade aircraft can rise to certain altitude fast in order to avoid colliding with the carrier tail wing. The jacking mechanism comprises a plurality of components which are required to be mutually matched according to respective preset working sequences to finish jacking the secondary aircraft, so that the time required for the secondary aircraft to reach the first target inclination angle is longer. The jet generator does not have complex mechanical movement during working, so that the starting speed is high, the jet can be provided for the secondary aircraft after starting, and the time required by the secondary aircraft to reach the safe height can be greatly shortened.
The jet generator that this application adopted sets up jack-up mechanism relatively has simple structure, the jet emission rate who provides is fast, the required energy is few, separation process aerodynamic drag and pneumatic heat are less, the thrust that acts on the second grade aircraft concentrates and the thrust size can be adjusted advantage such as according to the weight of second grade aircraft.
In practice, the jet generator is configured to provide an upward jet to a separation plane of the secondary aircraft forward of the center of gravity of the secondary aircraft. This jet generator can adopt cold jet generator also can be hot jet generator, because the second grade aircraft is recoverable spacecraft usually, its belly has the thermal-protective coating, and the temperature that can bear is higher, even adopt hot jet also can not cause the damage to the second grade aircraft. The jet flow generator provides jet flow for the secondary aircraft to act on the bottom of the secondary aircraft positioned in the front of the gravity center of the secondary aircraft, and the hinge mechanism is positioned at the tail of the secondary aircraft, so that the head raising moment of the secondary aircraft is larger. Further, the jet flow generator comprises a spray pipe nozzle, and the spray pipe nozzle is positioned on a normal projection extension line of the center of gravity of the back of the carrier. The jet pipe nozzle is positioned on the extension line of the normal projection of the gravity center of the carrier, so that the reaction force generated by the jet pipe nozzle after the jet flow acts on the secondary aircraft acts on the extension line of the normal projection of the gravity center of the carrier can be ensured to act on the extension line of the normal projection of the gravity center of the carrier, the carrier can be uniformly stressed without pitching, rolling and other phenomena under the reaction force, and the flight attitude and separation safety of the carrier are influenced. Specifically, the jet generator includes storage case and combustion chamber, the spray tube spout with the combustion chamber links to each other. The combustion chamber can burn through fuel supplied in the storage box, jet flow generated by combustion acts on the bottom of the secondary aircraft through the spraying nozzle of the spraying pipe, and the purpose of providing upward thrust for the secondary aircraft is achieved.
When the jet generator is used specifically, a plurality of sets of the jet generators can be selected and configured according to the weight of the carrier, so that the carrier can obtain enough thrust. For example, when the weight of the secondary aircraft is large, the generator needs to be made large in size by configuring one set of jet flow generator, so that the generator is not beneficial to being assembled with an aircraft, and at the moment, a plurality of sets of jet flow generators with small volumes can be selected to be matched for use to form a plurality of jet flows to act on the secondary aircraft together. The jet generator can also comprise a jet size adjusting mechanism (such as fuel flow adjustment) for adjusting the size of the jet provided by the jet generator, so that the jet generator arranged on the carrier is suitable for providing jet for secondary aircrafts with different weights. This regulation of efflux size can also be realized through the quantity of the many sets of efflux generators simultaneous workings that set up, for example, dispose 5 sets of efflux generators on certain carrier, when second grade aircraft weight is great, then can 5 sets of efflux generators provide the efflux to the second grade aircraft simultaneously, when second grade aircraft weight is less, can select one of them or several sets to provide the efflux to the second grade aircraft, can be in order to guarantee the quick separation of second grade aircraft, can practice thrift fuel again and prevent that the fluidic thrust from too big causing the damage to the second grade aircraft that provides. Meanwhile, the quick separation of the secondary aircrafts with different weights can be realized without changing the structure of the carrier.
In practical application, in order to realize the connection between the carrier and the secondary aircraft and simultaneously ensure the rapid separation and the relative rotation, the embodiment of the application can provide that a fixed connection mechanism 4 and a hinge mechanism 5 are formed between the respective separation surfaces of the carrier 1 and the secondary aircraft 3, and the hinge mechanism 5 is positioned at the tail of the secondary aircraft 3; the fixed connection mechanism 4 comprises a first self-releasing bolt, the first self-releasing bolt is used for enabling the jet flow and the hinge mechanism 5 to be balanced, the connection between the fixed connection mechanism and the carrier 1 and the secondary aircraft 3 is released after the gravity of the secondary aircraft, and the secondary aircraft 3 is enabled to rotate relatively by taking the hinge mechanism 5 as a fulcrum under the action of the jet flow so as to form the first target inclination angle. This link joint mechanism 4 can include first bracing piece and rather than adjacent first bolt of removing certainly, and the one end of first bracing piece can be with the anterior fixed continuous of year machine, and the first both ends of removing the bolt certainly link to each other with first bracing piece and second grade aircraft respectively. The second self-release bolt can be started after jet thrust and the gravity of the second-level aircraft can be balanced by the hinge mechanism at the tail part, so that the first support rod is completely separated from the second-level aircraft, the constraint force between the front end of the second-level aircraft and the aircraft disappears, and the second self-release bolt can rotate around the hinge mechanism under the thrust action provided by the jet so that the front part of the second-level aircraft is lifted up to finally form the first target inclination angle. The jet generator is required to provide a jet to the secondary aircraft at all times before the first target angle of inclination is reached, due to the small local angle of attack of the secondary aircraft.
The hinge mechanism comprises a second self-release bolt, and the second self-release bolt is used for releasing the connection of the hinge mechanism to the carrier and the secondary aircraft after the secondary aircraft and the carrier rotate relatively to form a second target inclination angle under the non-separated state. The hinge mechanism can comprise a second support rod, a hinge and a second self-releasing bolt, wherein one end of the second support rod is connected with the rear part of the carrier, the other end of the second support rod is connected with the hinge, and the two ends of the second self-releasing bolt are respectively connected with the hinge and the second-stage aircraft. After the inclination angle of the secondary aircraft reaches a second target inclination angle, the second self-release bolt can be started, so that the constraint force formed by the secondary aircraft and the hinge on the rear part of the secondary aircraft disappears, and the secondary aircraft can be completely separated from the carrier. After the inclination angle of the secondary aircraft reaches the first target inclination angle, the secondary aircraft continues to perform head-up movement under the action of inertia and aerodynamic force, so that the jet generator can be turned off in the process of transition from the first target inclination angle to the second target inclination angle. Therefore, fuel can be saved, the head raising speed of the secondary aircraft when the second self-release bolt is started can be reduced, and the phenomena that the pitch angle of the secondary aircraft is too large after separation and the longitudinal flight stability is reduced are avoided. In practical application, the first self-releasing bolt and the second self-releasing bolt are explosive bolts. The specific selection of which bolt can be selected according to the needs. Explosive bolts are often used for multipoint joining parting planes. Each explosive bolt is similar to a common bolt, and an explosive and an igniter are arranged in each explosive bolt. During separation, the explosive is detonated, so that the shear lock is sheared or broken along the bolt weakening groove, and the two separated bodies are unlocked. The explosive bolts are of various varieties and mainly comprise a slotted type explosive bolt, a shear pin type explosive bolt, a steel ball type explosive bolt, a pollution-free explosive bolt and the like. The device has the advantages of large bearing capacity, simple structure, reliable work and convenient use. In practical application, the explosion-free self-releasing bolt made of the titanium-nickel memory alloy can be selected, has the advantage of being reusable, and can not generate fragments after being started.
The embodiment of the application also provides a use method of the two-stage in-orbit aircraft back quick separation device, which comprises the following steps:
receiving separation instruction information; the separation instruction can be stored in the controller, and the separation instruction information can be acquired in a mechanical key triggering mode, a virtual key triggering mode or an automatic triggering mode according to the flight state; the mechanical key triggering mode can obtain the separation instruction information by pressing the corresponding triggering key; the virtual key triggering mode can realize the acquisition of the separation instruction information by pressing the relevant virtual triggering key in the interface of the corresponding software; the automatic triggering mode can automatically acquire the separation instruction information after meeting the triggering condition by judging the flight state of the carrier.
Controlling a jet flow generator to start according to the separation instruction information so that the jet flow emitter provides upward jet flow to the separation surface of the secondary aircraft; specifically, the controller can control the ignition device of the combustion chamber to ignite after receiving the instruction information, so that fuel in the combustion chamber is combusted, and jet flow can be sprayed out towards the secondary aircraft through the nozzle of the spray pipe, so that thrust is provided for the secondary aircraft.
After determining that the jet flow and the hinge mechanism can balance the gravity of the secondary aircraft, starting a first self-release bolt to release the connection of the fixed connection mechanism to the aircraft and the secondary aircraft; after the separation process begins, the jet flow is used for impacting the lower end of the front part of the secondary aircraft, when the thrust provided by the jet flow is enough to overcome the gravity (the pressure sensor arranged on the fixing mechanism acquires a signal, and when the pressure indicated by the pressure sensor is 0, the fixing mechanism does not bear the gravity), the first self-release bolt of the fixing mechanism between the secondary aircraft and the carrier is started to realize separation, so that the secondary aircraft rotates around the rear end hinge mechanism to realize head raising, the local attack angle is improved, and the lift force is increased.
Closing the jet flow generator after the secondary aircraft forms a first target inclination angle; under the action of jet flow, the secondary aircraft raises head, and when the secondary aircraft reaches the first target inclination angle, the jet flow generator can be closed.
And after the second-level aircraft forms a second target inclination angle, starting a second self-release bolt to release the connection of the hinge mechanism to the carrier and the second-level aircraft so as to realize the separation of the carrier and the second-level aircraft. The secondary aircraft continues to move head up under the action of inertia and aerodynamic force, and when the secondary aircraft reaches a second target inclination angle, the explosive bolt of the tail hinge mechanism finishes blasting separation; the secondary aircraft is separated from the carrier under the action of aerodynamic force.
In practical application, the first target inclination angle and the second target inclination angle are designed and preset by a simulation optimization method of coupling dynamics. Specifically, the first target inclination angle is the minimum inclination angle at which the secondary aircraft can rotate around the hinge mechanism to a second target inclination angle under the action of inertia and aerodynamic force; the second target inclination angle is the minimum inclination angle required by the secondary aircraft to generate the lift force for overcoming the self gravity of the secondary aircraft under the action of inertia and aerodynamic force. Further, the first target inclination angle and the second target inclination angle are measured through the secondary aircraft self-navigation system and the atmospheric system.
The separating device can be composed of a front fixing mechanism, a tail hinge mechanism and a jet generator. Wherein the front part fixing mechanism consists of a support rod and an explosive bolt. The tail hinge mechanism consists of a support rod, a hinge and an explosive bolt. The jet generator consists of a storage tank, a combustion chamber and a spray pipe, and the position of a spray nozzle of the spray pipe is positioned in the normal projection of the gravity center of the carrier. In the separation process, under the action of a control system, as shown in figure 1, a jet generator is started, jet generates upward thrust on a secondary aircraft, and when the jet thrust and a tail hinge mechanism can balance the gravity of the secondary aircraft, a front fixing mechanism explodes bolts to complete explosion separation; subsequently, as shown in fig. 2, under the action of the jet flow, the secondary aircraft raises its head, and when the secondary aircraft reaches a certain inclination angle, the jet flow generator is turned off; as shown in fig. 3, the secondary aircraft continues to move up under the action of inertia and aerodynamic force, and when a certain inclination angle is reached, the explosive bolt of the tail hinge mechanism completes blasting separation; and finally, the secondary aircraft is separated from the carrier under the action of aerodynamic force.
The effect pieces of the device and the method provided by the application are verified through flight dynamics simulation based on CFD. Under the conditions of Ma6.0, 30km height and 4-degree attack angle, the weight of the space shuttle is about 1.6t, and the carrier can be smoothly separated. The jet flow generator has the design jet flow Mach number of 3.0, jet flow pressure ratio of 1600, flow rate of 9.82kg/s and design jet flow operation of 0.248 s. Wherein the first target inclination angle is 2.59 deg., and the second target inclination angle is 12 deg.. Referring to fig. 4 and 5, after the tail hinge mechanism is separated, the time required for the space shuttle to reach the safe height is about 0.32 s.
It is noted that, herein, relational terms such as first and second, and the like may be used solely to distinguish one entity or action from another entity or action without necessarily requiring or implying any actual such relationship or order between such entities or actions. Also, the terms "comprises," "comprising," or any other variation thereof, are intended to cover a non-exclusive inclusion, such that a process, method, article, or apparatus that comprises a list of elements does not include only those elements but may include other elements not expressly listed or inherent to such process, method, article, or apparatus. Without further limitation, an element defined by the phrase "comprising an … …" does not exclude the presence of other identical elements in a process, method, article, or apparatus that comprises the element.
The above description is only a preferred embodiment of the present invention, and is not intended to limit the scope of the present invention. Any modification, equivalent replacement, or improvement made within the spirit and principle of the present invention shall fall within the protection scope of the present invention.
Claims (7)
1. A two-stage in-orbit aircraft back quick separation device, its characterized in that includes:
and the jet flow generator is used for providing upward jet flow for a separation surface of a secondary aircraft connected with the carrier so as to offset partial gravity of the secondary aircraft, so that the secondary aircraft and the carrier relatively rotate under an unseparated state to form a first target inclination angle so as to increase the lift force generated by the secondary aircraft.
2. The two-stage in-orbit aircraft back quick disconnect device of claim 1, wherein the jet generator is configured to provide an upward jet to a separation plane of the secondary aircraft forward of a center of gravity of the secondary aircraft.
3. The two-stage staging aircraft back quick disconnect of claim 2, wherein the jet generator includes a jet nozzle that is located on a center of gravity normal projection extension of the carrier back.
4. The two-stage staging aircraft back quick disconnect of claim 3, wherein the jet generator comprises a storage bin and a combustion chamber, the nozzle jets being connected to the combustion chamber.
5. The two-stage in-orbit aircraft back quick separation device according to claim 1, wherein a fixed connection mechanism and a hinge mechanism are formed between the respective separation surfaces of the carrier and the two-stage aircraft, and the hinge mechanism is positioned at the tail of the two-stage aircraft; the fixed connection mechanism comprises a first self-release bolt, the first self-release bolt is used for enabling the jet flow and the hinge mechanism to be balanced, the connection between the carrier and the secondary aircraft is released after the gravity of the secondary aircraft, and the secondary aircraft is enabled to rotate relatively by taking the hinge mechanism as a fulcrum under the action of the jet flow to form the first target inclination angle.
6. The two-stage in-orbit aircraft back quick separation device according to claim 5, wherein the hinge mechanism comprises a second self-release bolt for releasing the connection of the hinge mechanism to the aircraft and the secondary aircraft after the secondary aircraft and the aircraft are relatively rotated to form a second target inclination angle in an unseparated state.
7. The two-stage in-orbit aircraft back quick-disconnect device of claim 6, wherein the first self-disengaging bolt and the second self-disengaging bolt are explosive bolts.
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Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN115610693A (en) * | 2022-09-28 | 2023-01-17 | 成都飞机工业（集团）有限责任公司 | Thrust cone assembly for rocket launching unmanned aerial vehicle |
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2021
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Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN115610693A (en) * | 2022-09-28 | 2023-01-17 | 成都飞机工业（集团）有限责任公司 | Thrust cone assembly for rocket launching unmanned aerial vehicle |
| CN115610693B (en) * | 2022-09-28 | 2024-05-14 | 成都飞机工业（集团）有限责任公司 | Rocket launching unmanned aerial vehicle is with thrust cone subassembly |
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