CN104458193A - Wind tunnel multi-body separation free flight test device for stimulating engine residual thrust - Google Patents
Wind tunnel multi-body separation free flight test device for stimulating engine residual thrust Download PDFInfo
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- CN104458193A CN104458193A CN201410768702.4A CN201410768702A CN104458193A CN 104458193 A CN104458193 A CN 104458193A CN 201410768702 A CN201410768702 A CN 201410768702A CN 104458193 A CN104458193 A CN 104458193A
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Abstract
The invention discloses a wind tunnel multi-body separation free flight test device for stimulating engine residual thrust. The device comprises a secondary aircraft, a primary aircraft, a spring sleeve, a spring, a spring cover plate and a load. The secondary aircraft is detachably connected to the head of the primary aircraft through a first separation unlocking device, the spring sleeve is arranged on the tail of the primary aircraft, the rear end of the spring sleeve is provided with an opening, the spring is contained in the spring sleeve, the spring cover plate is detachably connected to the spring sleeve through a second separation unlocking device and at least partially covers the opening so as to enable the spring to be in the compressed state, and the load is connected with the spring cover plate. When the first separation unlocking device carries out unlocking to separate the secondary aircraft from the primary aircraft, the second separation unlocking device carries out unlocking to separate the primary aircraft from the load. The primary aircraft obtains separation energy, namely the certain separation speed under the spring energy, and research on the engine residual thrust is achieved.
Description
Technical field
The present invention relates to wind-tunnel Multi-bodies Separation free flight test device, particularly relate to a kind of wind-tunnel Multi-bodies Separation free flight test device of simulated engine thrust-drag margin, can be applicable to carrier rocket, guided missile and other Flight Vehicle Stage Separation thrust-drag margin interference characteristic wind-tunnel Multi-bodies Separation free flight tests.
Background technology
The aircraft such as carrier rocket, long-range intercontinental ballistic missile needs one-level aircraft (I level, is generally engine) to provide power in climbing flight section, and when climbing flight is to certain altitude, I level is separated (stage separation) with II level arrow body.In stage separation process, flow field is comparatively complicated, comprises the mutual interference of outflow, I stage motor jet flow and front and back secondary or multistage coupling part, relates to the phenomenons such as Shock wave interaction, separated flow and vortex.In I level and the detachment process of II level, I level is in II level afterbody flow field, also complicated transient state separation gas power can be formed between II level flight incoming flow and I level, this produces considerable influence to II level and I level movement locus and stalling characteristic, more very may there is residue jet flow thrust Δ F in I stage motor after cut-offfing, continuous firing a period of time Δ t, within the blink of thrust-drag margin continuous firing, an axial addition speed is produced to the I level one-level aircraft of " free flight ", how does this additional axial velocity affect if producing I level one-level aircraft movements track and stalling characteristic? this needs to answer.Unfortunately, this kind of experiment is conventional wind tunnel force measurement, pressure measurement experiment, domestic model test, grid dynamometry, CTS (captive trajectory) cannot simulate, and therefore needs by can the simulated flight device motion state of flying and meet the similar wind tunnel free flight test of kinematics and study truly aloft.
Summary of the invention
For above-mentioned technical matters, the invention provides a kind of one-level aircraft can obtain must separating force and disengaging time (or velocity of separation), thus realize the wind-tunnel Multi-bodies Separation free flight test device of one-level aircraft thrust-drag margin.
Technical scheme of the present invention is:
A wind-tunnel Multi-bodies Separation free flight test device for simulated engine thrust-drag margin, comprising:
Secondary aircraft and one-level aircraft, wherein, described secondary aircraft is separated by first the head that tripper is connected to described one-level aircraft separably;
Spring housing, it is arranged at the afterbody of described one-level aircraft, and the rearward end of described spring housing has opening;
Spring, it is located in described spring housing;
Spring bumper cover, it is separated tripper by second and is connected to described spring housing separably, covers described opening at least in part, is in compressive state to make described spring; And
Load, it is connected to described spring bumper cover;
Wherein, when described first is separated tripper unblock to make described secondary aircraft and described one-level aircraft be separated, described second is separated tripper unlocks to make described one-level aircraft and described load be separated.
Preferably, in the wind-tunnel Multi-bodies Separation free flight test device of described simulated engine thrust-drag margin, described one-level aircraft is equal with the quality of described load.
Preferably, the wind-tunnel Multi-bodies Separation free flight test device of described simulated engine thrust-drag margin, also comprises:
For launching the emitter of described one-level aircraft and described secondary aircraft.
Preferably, in the wind-tunnel Multi-bodies Separation free flight test device of described simulated engine thrust-drag margin, described emitter comprises straight line actuating unit, emitting head and launching tube, wherein, described emitting head is slidably disposed in described launching tube, described straight line actuating unit is connected to the opposite side of described emitting head, with to described emitting head output drive strength; Described load is a sliding axle, and described sliding axle is slidably disposed in described launching tube.
Preferably, in the wind-tunnel Multi-bodies Separation free flight test device of described simulated engine thrust-drag margin, described spring bumper cover and described sliding axle are for being threaded.
Preferably, in the wind-tunnel Multi-bodies Separation free flight test device of described simulated engine thrust-drag margin, described first is separated tripper comprises:
At least one pair of first through hole, is opened in the sidewall of the head of described one-level aircraft, is spaced certain angle arranges relative to the axis of described one-level aircraft;
At least one pair of second through hole, is opened in the sidewall of the afterbody of described secondary aircraft, and wherein, the afterbody of described secondary aircraft is sheathed on outside the head of described one-level aircraft;
At least one pair of first lock wire, each first lock wire is through first through hole and second through hole, and one end of this first lock wire is provided with the first stopper section limiting this first lock wire and depart from from this first through hole and this second through hole; And
First unlocks bracing wire, its one end is connected to the other end of all first lock wire, described first other end unlocking bracing wire extends to the outside of described one-level aircraft and described secondary aircraft, and the intensity of arbitrary first lock wire of strength ratio of described first unblock bracing wire is large;
Wherein, when described first is separated tripper unblock, unlocks bracing wire by described first and the first all lock wire is broken, thus described one-level aircraft and described secondary aircraft are separated.
Preferably, in the wind-tunnel Multi-bodies Separation free flight test device of described simulated engine thrust-drag margin, described second is separated tripper comprises:
At least one pair of the 3rd through hole, is opened in the sidewall of described spring housing, is spaced certain angle arranges relative to the axis of described spring housing;
At least one pair of the 4th through hole, is opened in described spring bumper cover;
At least one pair of second lock wire, each second lock wire is through the 3rd through hole and the 4th through hole, and one end of this second lock wire is provided with the second stopper section limiting this second lock wire and depart from from the 3rd through hole and the 4th through hole; And
Second unlocks bracing wire, and its one end is connected to the other end of all first lock wire, and described second other end unlocking bracing wire extends to the outside of described one-level aircraft, and the intensity of arbitrary second lock wire of strength ratio of described second unblock bracing wire is large;
Wherein, when described second is separated tripper unblock, unlocks bracing wire by described second and the second all lock wire is broken, thus described one-level aircraft and described load are separated.
Preferably, in the wind-tunnel Multi-bodies Separation free flight test device of described simulated engine thrust-drag margin, described one-level aircraft is the cylinder-like structure of inner hollow.
Preferably, in the wind-tunnel Multi-bodies Separation free flight test device of described simulated engine thrust-drag margin, the part of described opening cover by described spring bumper cover; The leading section of described spring housing offers the 5th through hole, described first unlocks bracing wire passes from the inside of described one-level aircraft, through described 5th through hole, and extend to the outside of described one-level aircraft and described secondary aircraft via another part of described opening.
Preferably, in the wind-tunnel Multi-bodies Separation free flight test device of described simulated engine thrust-drag margin, described first lock wire is for be made up of molybdenum filament, and described first unlocks bracing wire for be made up of molybdenum filament, and described first unlocks the number of share of stock of the molybdenum filament of bracing wire more than described first lock wire; Described second lock wire is for be made up of molybdenum filament, and described second unlocks bracing wire for be made up of molybdenum filament, and described second unlocks the number of share of stock of the molybdenum filament of bracing wire more than described second lock wire.
Technique effect of the present invention is:
(1) one-level aircraft is connected by the first separation tripper separably with secondary aircraft, the afterbody of one-level aircraft is provided with spring housing, spring is located in spring housing, spring bumper cover is separated tripper by second and is connected to spring housing separably, and apply pressure to spring, thus make spring be in compressive state, when first be separated tripper to be separated with second tripper unlock simultaneously time, one-level aircraft and secondary aircraft are separated, one-level aircraft and load are also separated, one-level aircraft can obtain separation energy down at spring, namely one-level aircraft obtains certain velocity of separation.One-level aircraft is used for simulated engine, achieves the research to engine residual thrust.
(2) by adjusting the quality of one-level aircraft and load, change the velocity of separation of one-level aircraft, and then realize the research in varied situations of one-level aircraft.
Accompanying drawing explanation
Fig. 1 is the structural representation of an embodiment of the wind-tunnel Multi-bodies Separation free flight test device of simulated engine thrust-drag margin of the present invention;
Fig. 2 is the structural representation of emitter of the present invention.
Embodiment
For enabling above-mentioned purpose of the present invention, feature and advantage become apparent more, are described in detail the specific embodiment of the present invention below in conjunction with accompanying drawing.
Refer to Fig. 1, the invention provides a kind of wind-tunnel Multi-bodies Separation free flight test device of simulated engine thrust-drag margin, comprise: secondary aircraft 7 and one-level aircraft 8, wherein, described secondary aircraft 7 is separated by first the head that tripper is connected to described one-level aircraft 8 separably; Spring housing 9, it is arranged at the afterbody of described one-level aircraft 8, and the rearward end of described spring housing has opening; Spring 10, it is located in described spring housing 9; Spring bumper cover 6, it is separated tripper by second and is connected to described spring housing 9 separably, covers described opening at least in part, is in compressive state to make described spring 10; And load, it is connected to described spring bumper cover; Wherein, when described first is separated tripper unblock to make described secondary aircraft and described one-level aircraft be separated, described second is separated tripper unlocks to make described secondary aircraft and described load be separated.In order to test the aerial sports state of one-level aircraft under thrust-drag margin, while one-level aircraft is separated with secondary aircraft, one-level aircraft is also separated with load, and namely two separation occur simultaneously.
In test unit of the present invention, one-level aircraft simulation engine, secondary aircraft simulation bullet rocket body.
One-level aircraft obtains separation energy (i.e. velocity of separation) under the effect of spring energy, when two objects are under pretensioned spring connects, after retracting spring, two objects can move along contrary direction, if when being no longer subject to other External Force Actings, time compole in short-term, two articles motion meets the law of conservation of momentum and law of conservation of energy, and when two mass of objects are equal, the velocity amplitude that each chorista obtains is equal, energy is maximum, equals the half of pre-compressed spring energy.Therefore, in order to obtain suitable separation energy, the quality of one-level aircraft and load can be adjusted.
The parameter such as thrust-drag margin amount, thrust-drag margin active position of one-level aircraft is by realizing the calculating of spring parameter and spring centroid position.Spring rate K is designed by the parameter such as design wire diameter d, mean diameter of coil D, number of coils n, and design compression deformation of the spring amount Δ X, make the velocity of separation needed for roll booster acquisition and angle of departure speed, thus realize engine residual thrust wind tunnel test simulation.
In addition, spring bumper cover can cover the opening on spring housing completely, applies pressure to spring; Also partly can cover the opening of spring housing, the opening of such as spring housing is rounded, and spring bumper cover has rectangular shape, then two minor faces of spring bumper cover can be connected to spring housing, then remain with space between long limit and spring housing.
In one embodiment, in the wind-tunnel Multi-bodies Separation free flight test device of described simulated engine thrust-drag margin, described one-level aircraft is equal with the quality of described load, and maximum with the velocity of separation making one-level aircraft can descend to obtain at certain spring, separation energy is maximum.
In one embodiment, the wind-tunnel Multi-bodies Separation free flight test device of described simulated engine thrust-drag margin, also comprises: for launching the emitter of described one-level aircraft and described secondary aircraft.Emitter of the present invention can adopt emission coefficient of the prior art.
Refer to Fig. 2, in one embodiment, in the wind-tunnel Multi-bodies Separation free flight test device of described simulated engine thrust-drag margin, described emitter comprises straight line actuating unit, emitting head 4 and launching tube 5, wherein, described emitting head 4 is slidably disposed in described launching tube 5, and described straight line actuating unit is connected to the opposite side of described emitting head, with to described emitting head output drive strength; Described load is a sliding axle 12, and described sliding axle 12 is slidably disposed in described launching tube.Particularly, sliding axle 12 is slidably disposed in launching tube, is achieved in the following ways: sliding axle 12 is slidably disposed in a sliding shaft sleeve 13, and sliding shaft sleeve 13 is fixed on launching tube 5, not mobile with the movement of emitting head.In addition, above-mentioned straight line actuating unit is preferably cylinder, and it specifically comprises cylinder body 3 and is slidably disposed on the piston 1 in cylinder body 3, and the front side of piston 1 is connected to a piston rod 2, and piston rod 2 stretches out in cylinder body 3, and is connected to emitting head 4.In gases at high pressure input cylinder body, promote piston to travel forward fast along inboard wall of cylinder block, emitting head promotes load, one-level aircraft and secondary aircraft travel forward, at one-level aircraft, after emitter is left in secondary aircraft and load, aloft fly a period of time, when moving near wind tunnel window, first separation tripper and second is separated tripper and unlocks simultaneously, make one-level aircraft and secondary aircraft being separated without relative motion, one-level aircraft and load be relative counter motion under the action of the spring, one-level aircraft obtains corresponding separating force and disengaging time, thus ensure the realization of thrust-drag margin.This process is controlled by hyperchannel precise synchronization controller, the synchronous or delayed startup by high-speed camera, to realize the time of releasing and two-stage aircraft movements track shooting after being separated.
In one embodiment, in the wind-tunnel Multi-bodies Separation free flight test device of described simulated engine thrust-drag margin, described spring bumper cover and described sliding axle for being threaded, thus are convenient to change sliding axle.
Refer to Fig. 1, in one embodiment, preferably, in the wind-tunnel Multi-bodies Separation free flight test device of described simulated engine thrust-drag margin, described first is separated tripper comprises: at least one pair of first through hole, be opened in the sidewall of the head of described one-level aircraft, be spaced certain angle relative to the axis of described one-level aircraft and arrange; At least one pair of second through hole, is opened in the sidewall of the afterbody of described secondary aircraft, and wherein, the afterbody of described secondary aircraft is sheathed on outside the head of described one-level aircraft; At least one pair of first lock wire 14, each first lock wire is through first through hole and second through hole, and one end of this first lock wire is provided with the first stopper section limiting this first lock wire and depart from from this first through hole and this second through hole; And first unlocks bracing wire 15, its one end is connected to the other end of all first lock wire, described first other end unlocking bracing wire extends to the outside of described one-level aircraft and described secondary aircraft, and the intensity of arbitrary first lock wire of strength ratio of described first unblock bracing wire is large; Wherein, when described first is separated tripper unblock, unlocks bracing wire by described first and the first all lock wire is broken, thus described one-level aircraft and described secondary aircraft are separated.
In this embodiment, for the first stopper section, comparatively simple mode is exactly tied a knot one end of the first lock wire, and the button formed is the first stopper section.In addition, preferably, at least one pair of first through hole is the first through hole that two axis at intervals 180 ° relative to one-level aircraft distribute; Correspondingly, at least one pair of second through hole is also two the second through holes, and the first through hole and the second through hole are setting of aliging one by one.
Bracing wire is unlocked for first, when the first stopper section is the outside being positioned at secondary aircraft, in order to be connected with the first lock wire, first unlocks the inside that bracing wire is positioned at one-level aircraft, then it can pass the outside to one-level aircraft from the hole be opened in one-level aircraft sidewall, so that pull the first unblock bracing wire when unlocking; When the first stopper section is the inside being positioned at one-level aircraft, then first unlock the outside that bracing wire entirety is positioned at one-level aircraft and described secondary aircraft.The previous case is more convenient for operating, and can ensure that the first all lock wire is pulled off simultaneously.
In one embodiment, in the wind-tunnel Multi-bodies Separation free flight test device of described simulated engine thrust-drag margin, described second is separated tripper comprises: at least one pair of the 3rd through hole, be opened in the sidewall of described spring housing, be spaced certain angle relative to the axis of described spring housing and arrange; At least one pair of the 4th through hole, is opened in described spring bumper cover; At least one pair of second lock wire, each second lock wire 11 is through the 3rd through hole and the 4th through hole, and one end of this second lock wire is provided with the second stopper section limiting this second lock wire and depart from from the 3rd through hole and the 4th through hole; And second unlocks bracing wire 16, its one end is connected to the other end of all first lock wire, and described second other end unlocking bracing wire extends to the outside of described one-level aircraft, and the intensity of arbitrary second lock wire of strength ratio of described second unblock bracing wire 16 is large; Wherein, when described second is separated tripper unblock, unlocks bracing wire by described second and the second all lock wire is broken, thus described one-level aircraft and described load are separated.For the second stopper section, comparatively simple mode is exactly tied a knot one end of the second lock wire, and the button formed is the second stopper section.In addition, preferably, at least one pair of the 3rd through hole is the 3rd through hole that two axis at intervals 180 ° relative to spring housing distribute; Correspondingly, at least one pair of the 4th through hole is also two the 4th through holes, and the 3rd through hole and the 4th through hole are setting of aliging one by one.When spring bumper cover is designed to rectangle, the 4th through hole is arranged near the minor face of spring bumper cover, to realize the connection of spring bumper cover and spring housing.
Being separated tripper to make the first separation tripper and second to unlock simultaneously, needing to pull the first unblock bracing wire and second to unlock bracing wire simultaneously.
In one embodiment, in the wind-tunnel Multi-bodies Separation free flight test device of described simulated engine thrust-drag margin, described one-level aircraft is the cylinder-like structure of inner hollow, with the engine (or roll booster) of reality, there is basically identical shape, but do not possess the inner structure of actual engine (or roll booster), can realize being as the criterion to the simulation of disengaging movement.
In one embodiment, in the wind-tunnel Multi-bodies Separation free flight test device of described simulated engine thrust-drag margin, the part of described opening cover by described spring bumper cover; The leading section of described spring housing offers the 5th through hole, described first unlocks bracing wire passes from the inside of described one-level aircraft, through described 5th through hole, and the outside of described one-level aircraft and described secondary aircraft is extended to via another part of described opening, thus hole must do not offered on the sidewall of one-level aircraft or other positions, unlock bracing wire for first and pass.
In one embodiment, in the wind-tunnel Multi-bodies Separation free flight test device of described simulated engine thrust-drag margin, described first lock wire is for be made up of molybdenum filament, and described first unlocks bracing wire for be made up of molybdenum filament, and described first unlocks the number of share of stock of the molybdenum filament of bracing wire more than described first lock wire; Described second lock wire is for be made up of molybdenum filament, and described second unlocks bracing wire for be made up of molybdenum filament, and described second unlocks the number of share of stock of the molybdenum filament of bracing wire more than described second lock wire.In order to ensure the first lock wire, the second lock wire has enough intensity, and ensure that the previous stage aircraft that do not unlock and secondary aircraft can normal flights, the two can adopt molybdenum filament to make, but also can adopt other materials.Simultaneously in order to ensure that the first unblock bracing wire can break the first lock wire, namely the first unblock bracing wire is larger than the intensity of the first lock wire, can be realized by the number of share of stock increasing by the first unblock bracing wire, or be that the first lock wire adopts a kind of material, and be that the first unblock bracing wire adopts the better material of another kind of intensity to realize.No matter be which kind of situation, for ensureing that the first lock wire and the second lock wire rupture simultaneously, under identical pulling force, the first lock wire should be the same with the material selected by the second lock wire or number of share of stock, and the first unblock bracing wire and material selected by the second unblock bracing wire or number of share of stock is the same.
In the present invention, for stating conveniently, with the left side of Fig. 1 and Fig. 2 for head or front, with right side be tail or after, but the enforcement of technical scheme of the present invention does not limit the orientation shown in Fig. 1 and Fig. 2.
Although the present invention with preferred embodiment openly as above; but it is not for limiting the present invention; any those skilled in the art without departing from the spirit and scope of the present invention; possible variation and amendment can be made; therefore, the scope that protection scope of the present invention should define with the claims in the present invention is as the criterion.
Claims (10)
1. a wind-tunnel Multi-bodies Separation free flight test device for simulated engine thrust-drag margin, is characterized in that, comprising:
Secondary aircraft and one-level aircraft, wherein, described secondary aircraft is separated by first the head that tripper is connected to described one-level aircraft separably;
Spring housing, it is arranged at the afterbody of described one-level aircraft, and the rearward end of described spring housing has opening;
Spring, it is located in described spring housing;
Spring bumper cover, it is separated tripper by second and is connected to described spring housing separably, covers described opening at least in part, is in compressive state to make described spring; And
Load, it is connected to described spring bumper cover;
Wherein, when described first is separated tripper unblock to make described secondary aircraft and described one-level aircraft be separated, described second is separated tripper unlocks to make described one-level aircraft and described load be separated.
2. the wind-tunnel Multi-bodies Separation free flight test device of simulated engine thrust-drag margin as claimed in claim 1, it is characterized in that, described one-level aircraft is equal with the quality of described load.
3. the wind-tunnel Multi-bodies Separation free flight test device of simulated engine thrust-drag margin as claimed in claim 1 or 2, is characterized in that, also comprise:
For launching the emitter of described one-level aircraft and described secondary aircraft.
4. the wind-tunnel Multi-bodies Separation free flight test device of simulated engine thrust-drag margin as claimed in claim 3, it is characterized in that, described emitter comprises straight line actuating unit, emitting head and launching tube, wherein, described emitting head is slidably disposed in described launching tube, described straight line actuating unit is connected to the opposite side of described emitting head, with to described emitting head output drive strength; Described load is a sliding axle, and described sliding axle is slidably disposed in described launching tube.
5. the wind-tunnel Multi-bodies Separation free flight test device of simulated engine thrust-drag margin as claimed in claim 4, it is characterized in that, described spring bumper cover and described sliding axle are for being threaded.
6. the wind-tunnel Multi-bodies Separation free flight test device of simulated engine thrust-drag margin as claimed in claim 1 or 2, is characterized in that, described first is separated tripper comprises:
At least one pair of first through hole, is opened in the sidewall of the head of described one-level aircraft, is spaced certain angle arranges relative to the axis of described one-level aircraft;
At least one pair of second through hole, is opened in the sidewall of the afterbody of described secondary aircraft, and wherein, the afterbody of described secondary aircraft is sheathed on outside the head of described one-level aircraft;
At least one pair of first lock wire, each first lock wire is through first through hole and second through hole, and one end of this first lock wire is provided with the first stopper section limiting this first lock wire and depart from from this first through hole and this second through hole; And
First unlocks bracing wire, its one end is connected to the other end of all first lock wire, described first other end unlocking bracing wire extends to the outside of described one-level aircraft and described secondary aircraft, and the intensity of arbitrary first lock wire of strength ratio of described first unblock bracing wire is large;
Wherein, when described first is separated tripper unblock, unlocks bracing wire by described first and the first all lock wire is broken, thus described one-level aircraft and described secondary aircraft are separated.
7. the wind-tunnel Multi-bodies Separation free flight test device of simulated engine thrust-drag margin as claimed in claim 5, is characterized in that, described second is separated tripper comprises:
At least one pair of the 3rd through hole, is opened in the sidewall of described spring housing, is spaced certain angle arranges relative to the axis of described spring housing;
At least one pair of the 4th through hole, is opened in described spring bumper cover;
At least one pair of second lock wire, each second lock wire is through the 3rd through hole and the 4th through hole, and one end of this second lock wire is provided with the second stopper section limiting this second lock wire and depart from from the 3rd through hole and the 4th through hole; And
Second unlocks bracing wire, and its one end is connected to the other end of all first lock wire, and described second other end unlocking bracing wire extends to the outside of described one-level aircraft, and the intensity of arbitrary second lock wire of strength ratio of described second unblock bracing wire is large;
Wherein, when described second is separated tripper unblock, unlocks bracing wire by described second and the second all lock wire is broken, thus described one-level aircraft and described load are separated.
8. the wind-tunnel Multi-bodies Separation free flight test device of simulated engine thrust-drag margin as claimed in claim 7, it is characterized in that, described one-level aircraft is the cylinder-like structure of inner hollow.
9. the wind-tunnel Multi-bodies Separation free flight test device of simulated engine thrust-drag margin as claimed in claim 8, is characterized in that, the part of described opening cover by described spring bumper cover; The leading section of described spring housing offers the 5th through hole, described first unlocks bracing wire passes from the inside of described one-level aircraft, through described 5th through hole, and extend to the outside of described one-level aircraft and described secondary aircraft via another part of described opening.
10. the wind-tunnel Multi-bodies Separation free flight test device of simulated engine thrust-drag margin as claimed in claim 7, it is characterized in that, described first lock wire is for be made up of molybdenum filament, described first unlocks bracing wire for be made up of molybdenum filament, and described first unlocks the number of share of stock of the molybdenum filament of bracing wire more than described first lock wire; Described second lock wire is for be made up of molybdenum filament, and described second unlocks bracing wire for be made up of molybdenum filament, and described second unlocks the number of share of stock of the molybdenum filament of bracing wire more than described second lock wire.
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| CN107505116A (en) * | 2017-09-04 | 2017-12-22 | 中国空气动力研究与发展中心高速空气动力研究所 | The aircraft support meanss and transonic wind tunnel experimental provision of air formation flight experiment |
| CN117875222A (en) * | 2024-03-12 | 2024-04-12 | 中国空气动力研究与发展中心计算空气动力研究所 | Long-distance interstage separation track numerical value prediction method and equipment |
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| CN107505116A (en) * | 2017-09-04 | 2017-12-22 | 中国空气动力研究与发展中心高速空气动力研究所 | The aircraft support meanss and transonic wind tunnel experimental provision of air formation flight experiment |
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| CN117875222B (en) * | 2024-03-12 | 2024-05-17 | 中国空气动力研究与发展中心计算空气动力研究所 | Long-distance interstage separation track numerical value prediction method and equipment |
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