CN2506543Y - Launching test stand for astronautic air vehicle - Google Patents
Launching test stand for astronautic air vehicle Download PDFInfo
- Publication number
- CN2506543Y CN2506543Y CN 01264524 CN01264524U CN2506543Y CN 2506543 Y CN2506543 Y CN 2506543Y CN 01264524 CN01264524 CN 01264524 CN 01264524 U CN01264524 U CN 01264524U CN 2506543 Y CN2506543 Y CN 2506543Y
- Authority
- CN
- China
- Prior art keywords
- launching
- stand
- missile
- velocity
- launcher
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Expired - Fee Related
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Abstract
The utility model relates to a launching device, in particularly to a launching test stand for astronautic air vehicle, which comprises a circular disc type stand. A launcher is fixed on the launching stand by the circular disc type stand. The circular disc type stand can provide an initial velocity for the launcher by rotation of a transmission device. When the required velocity is reached by a linear velocity of the rotation of the launcher, the launcher can be launched by an ejection device. An adjustable included angle is arranged between the launching stand and a horizontal plane. The initial velocity required for launching of a spacecraft and a missile can be provided by the launching stand, number of a propulsion rocket used for provision of the initial velocity of the spacecraft and missile is reduced, the structure is simplified, the weight is lightened and the launching cost is reduced. The utility model can achieve the ground simulation of air flying state, artificial control of the velocity, and multiple-using for one-time investment in the field of scientific experiment of the stand.
Description
Technical field
The utility model relates to feedway, particularly a kind of aerospacecraft launching test platform.
Background technology
Launch spacecraft and guided missile etc. at present both at home and abroad, generally all adopt rocket as powered spacecraft and guided missile etc., to satisfy in its flight course requirement to speed, this just makes the total weight of spacecraft and guided missile mainly concentrate on the rocket that advances its flight, cause the weight of spacecraft and guided missile to increase on the one hand, very expensive when at every turn launching on the other hand, and when making some flight test, the collection of data be difficulty also.
Summary of the invention
The utility model is to adopt a garden plate-like platform, missile is fixed on the flat pad, when garden plate-like platform rotates by a driving device, just can provides an initial velocity to missile, when the linear velocity of missile rotation reaches when needing, just can it be launched by catapult-launching gear; The angle of this flat pad and horizontal surface is adjustable.
This flat pad can be spacecraft and guided missile provides initial velocity required when launching, make spacecraft and guided missile be used to its booster rocket quantity that initial velocity is provided to reduce, simple, the deadweight that structure is become reduces, launch cost reduces, and this platform is aspect scientific experiment, can be implemented in ground simulation airflight state, speed can artificially be controlled, and once drops into repeated use.
Description of drawings
Accompanying drawing 1 is the front view of the utility model embodiment one.
Accompanying drawing 2 is the birds-eye view of the utility model embodiment one.
Accompanying drawing 3 is the front view of the utility model embodiment two.
Accompanying drawing 4 is the front view of the utility model embodiment three.
Specific embodiment
Embodiment one:
As shown in Figure 1, 2, be symmetrically fixed with missile 1 and mass 2 at the edge of garden plate-like platform 3, missile 1 is fixed on fixed mount and the catapult-launching gear 4, garden plate-like platform 3 makes its rotation by a mechanical drive 5, when the linear velocity of missile 1 reaches emission and needs, anchor fitting is opened automatically, just can missile 1 be launched away by catapult-launching gear 4 by the required direction of emission, because required initial velocity is to be provided by the launching test platform during emission, just can deduct the rocket that initial velocity is provided for it on the missile 1; The angle of garden plate-like flat pad 3 and horizontal surface is at 0 °; When needs are done the flight test of relevant aerospacecraft or guided missile, can some experimental apparatuss be installed on garden plate-like flat pad 3 directly, it is carried out data acquisition.When the diameter of garden plate-like flat pad 3 was enough big, the linear velocity on its circumference can reach first, second and third cosmic velocity.
Embodiment two:
As shown in Figure 3, be symmetrically fixed with missile 1 and mass 2 at the edge of garden plate-like platform 3, missile 1 is fixed on fixed mount and the catapult-launching gear 4, and garden plate-like platform 3 makes its rotation by a magnetic suspension superconducting device 6, so just can improve rotative speed, reduce resistance; When the linear velocity of missile 1 reaches emission and needs, anchor fitting is opened automatically, just can missile 1 be launched away by the required direction of emission by catapult-launching gear 4, required initial velocity is to be provided by the launching test platform during owing to emission, just can deduct the rocket that initial velocity is provided for it on the missile 1; Garden plate-like flat pad 3 by a support body support can with the angle of horizontal surface at 45 °.
Embodiment three:
As shown in Figure 4, be symmetrically fixed with missile 1 and mass 2 at the edge of garden plate-like platform 3, missile 1 is fixed on fixed mount and the catapult-launching gear 4, and garden plate-like platform 3 makes its rotation by a magnetic suspension superconducting device 6, so just can improve rotative speed, reduce resistance; When the linear velocity of missile 1 reaches emission and needs, anchor fitting is opened automatically, just can missile 1 be launched away by the required direction of emission by catapult-launching gear 4, required initial velocity is to be provided by the launching test platform during owing to emission, just can deduct the rocket that initial velocity is provided for it on the missile 1; Garden plate-like flat pad 3 by a support body support can with the angle of horizontal surface at 90 °.
Claims (5)
1. an aerospacecraft launching test platform is characterized in that being fixed with missile fixed mount and catapult-launching gear (4) on the garden plate-like flat pad (3), under garden plate-like flat pad (3) wheel word that can make its rotation is installed.
2. a kind of aerospacecraft launching test platform according to claim 1 is characterized in that can make the driving device of garden plate-like flat pad (3) rotation is a mechanical drive.
3. a kind of aerospacecraft launching test platform according to claim 2 is characterized in that mechanical drive is by the driven by motor reductor, the reductor driven gear, and gear meshes with the gear that is fixed under the flat pad.
4. a kind of aerospacecraft launching test platform according to claim 1 is characterized in that can make the driving device of garden plate-like flat pad (3) rotation is a magnetic suspension superconducting device (6).
5. a kind of aerospacecraft launching test platform according to claim 1, the angle that it is characterized in that garden plate-like flat pad (3) and horizontal surface is at 0-90 °.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN 01264524 CN2506543Y (en) | 2001-08-27 | 2001-08-27 | Launching test stand for astronautic air vehicle |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN 01264524 CN2506543Y (en) | 2001-08-27 | 2001-08-27 | Launching test stand for astronautic air vehicle |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN2506543Y true CN2506543Y (en) | 2002-08-21 |
Family
ID=33671784
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN 01264524 Expired - Fee Related CN2506543Y (en) | 2001-08-27 | 2001-08-27 | Launching test stand for astronautic air vehicle |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN2506543Y (en) |
Cited By (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN101286281B (en) * | 2008-06-03 | 2010-04-14 | 清华大学 | Rigid-elastic liquid coupled spacecraft physical simulation experiment system |
| CN101499220B (en) * | 2009-01-24 | 2010-09-29 | 哈尔滨工业大学 | Method and apparatus for simulating large thruster on spacecraft |
| CN102556360A (en) * | 2012-02-06 | 2012-07-11 | 董兰田 | Orbit accelerating airplane capable of completing lift-off of two-stage rocket spacecraft with two-stage moving platforms |
| CN102689698A (en) * | 2012-05-22 | 2012-09-26 | 北京航空航天大学 | Ground emitting control device of solid-liquid powered aircraft |
| CN105021089A (en) * | 2014-04-30 | 2015-11-04 | 王力丰 | High-muzzle-velocity pellet launching device and launching method |
| CN110254754A (en) * | 2019-06-24 | 2019-09-20 | 北京机械设备研究所 | A kind of Space Rotating release device and rotation method for releasing |
-
2001
- 2001-08-27 CN CN 01264524 patent/CN2506543Y/en not_active Expired - Fee Related
Cited By (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN101286281B (en) * | 2008-06-03 | 2010-04-14 | 清华大学 | Rigid-elastic liquid coupled spacecraft physical simulation experiment system |
| CN101499220B (en) * | 2009-01-24 | 2010-09-29 | 哈尔滨工业大学 | Method and apparatus for simulating large thruster on spacecraft |
| CN102556360A (en) * | 2012-02-06 | 2012-07-11 | 董兰田 | Orbit accelerating airplane capable of completing lift-off of two-stage rocket spacecraft with two-stage moving platforms |
| CN102556360B (en) * | 2012-02-06 | 2014-04-02 | 董兰田 | Orbit accelerating airplane capable of completing lift-off of two-stage rocket spacecraft with two-stage moving platforms |
| CN102689698A (en) * | 2012-05-22 | 2012-09-26 | 北京航空航天大学 | Ground emitting control device of solid-liquid powered aircraft |
| CN105021089A (en) * | 2014-04-30 | 2015-11-04 | 王力丰 | High-muzzle-velocity pellet launching device and launching method |
| CN110254754A (en) * | 2019-06-24 | 2019-09-20 | 北京机械设备研究所 | A kind of Space Rotating release device and rotation method for releasing |
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Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| C14 | Grant of patent or utility model | ||
| GR01 | Patent grant | ||
| C19 | Lapse of patent right due to non-payment of the annual fee | ||
| CF01 | Termination of patent right due to non-payment of annual fee |