# EDGAR Filing Document

**Accession Number:** 0001814329
**File Stem:** 0001193125-23-056517
**Filing Date:** 2023-3
**Character Count:** 20929
**Document Hash:** 07e114acd8cb95d74bb463e33f14a633
**Contains OCR:** False
**Source Format:** 

## Filing Content

## Filing Summary
**0001193125-23-056517.hdr.sgml**: 20230301

**ACCESSION NUMBER**: 0001193125-23-056517

**CONFORMED SUBMISSION TYPE**: 424B3

**PUBLIC DOCUMENT COUNT**: 4

**FILED AS OF DATE**: 20230301

**DATE AS OF CHANGE**: 20230301

**FILER**: 

**COMPANY DATA:**
- **COMPANY CONFORMED NAME:** Astra Space, Inc.
- **CENTRAL INDEX KEY:** 0001814329
- **STANDARD INDUSTRIAL CLASSIFICATION:** TRANSPORTATION SERVICES [4700]
- **IRS NUMBER:** 141916687
- **FISCAL YEAR END:** 1231

**FILING VALUES:**
- **FORM TYPE:** 424B3
- **SEC ACT:** 1933 Act
- **SEC FILE NUMBER:** 333-257930
- **FILM NUMBER:** 23694752

**BUSINESS ADDRESS:**
- **STREET 1:** 1900 SKYHAWK STREET
- **CITY:** ALAMEDA
- **STATE:** CA
- **ZIP:** 94501
- **BUSINESS PHONE:** (866) 278-7217

**MAIL ADDRESS:**
- **STREET 1:** 1900 SKYHAWK STREET
- **CITY:** ALAMEDA
- **STATE:** CA
- **ZIP:** 94501

**FORMER COMPANY:**
- **FORMER CONFORMED NAME:** Holicity Inc.
- **DATE OF NAME CHANGE:** 20200608

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| | |
|:---|:---|
|  | **Filed Pursuant to Rule (424)(b)(3)** |
| **PROSPECTUS SUPPLEMENT NO. 24** | **Registration No. 333-257930** |
| **(to Prospectus dated July 14, 2022)** |  |

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**ASTRA SPACE, INC.**

***Primary Offering Of***

**15,333,303 Shares of Class A Common Stock**

***Secondary Offering of***

**189,026,575 Shares of Class A Common Stock**

This prospectus supplement amends and supplements the prospectus dated July 14, 2022 (as supplemented or amended from time to time, the "Prospectus"), which forms a part of our Registration Statement on Form S-1 (No. 333-257930). This prospectus supplement is being filed to update and supplement the information in the Prospectus with the information contained in our Current Report on Form 8-K, filed with the Securities and Exchange Commission (the "SEC") on March 1, 2023 (the "Current Report"). Accordingly, we have attached the Current Report to this prospectus supplement.

The Prospectus and this prospectus supplement also relate to the offer and sale, from time to time, by the selling securityholders named in this prospectus (the "Selling Securityholders"), or any of their permitted transferees, of (i) up to an aggregate of 20,000,000 shares of our Class A common stock that were issued to certain investors (collectively, the "PIPE Investors") in a private placement in connection with the closing of the Business Combination (as defined herein); (ii) 7,500,000 shares of Class A common stock issued to the Sponsor prior to Holicity's initial public offering and registered for sale by the Selling Securityholders; (iii) up to an aggregate of 92,277,793 shares of Class A common stock that were issued to certain affiliates of Astra (collectively, the "Astra Affiliates") pursuant to the Business Combination Agreement (as defined herein); (iv) up to an aggregate 56,239,188 shares of Class A common stock issuable upon conversion (on a one-for-one basis) of shares of our Class B common stock, par value $0.0001 per share ("Class B Common Stock") held by certain Selling Securityholders and (v) up to an aggregate of 7,676,261 shares of our Class A common stock issued in connection with our acquisition of Apollo Fusion, Inc. ("Apollo Fusion"), which closed on July 1, 2021 comprised of (x) 2,558,744 shares of our Class A common stock (the "Initial Apollo Shares") issued to certain of the Selling Securityholders on July 1, 2021, in connection with our merger with Apollo Fusion, Inc. ("Apollo Fusion") and (y) 5,117,517 additional shares of our Class A common stock (the "Additional Apollo Shares") which may be issued to certain of the Selling Securityholders assuming (a) the achievement of all remaining performance milestones set forth in the Apollo Fusion Merger Agreement (as defined herein), (b) we elect to pay all future milestone consideration in shares of our Class A common stock as required by the terms the Apollo Fusion Merger Agreement, and (c) the per share price used to calculate the number of shares of our Class A common stock to be issued is $11.7243, which is the same per share price used to calculate the number of Initial Shares issued to the Selling Securityholders. The Additional Shares have not been earned and are not currently outstanding. The actual number of Additional Shares issued to the selling stockholders could be materially greater or less than 5,117,517 shares of Class A common stock depending whether and to what extent the future performance milestones are met and/or the actual average closing price of our Class A common stock at the time such milestones are achieved. The Prospectus and this prospectus supplement also cover any additional securities that may become issuable by reason of share splits, share dividends or other similar transactions.

Our Class A common stock is listed on Nasdaq under the symbol "ASTR". On February 28, 2023, the closing price of our Class A common stock was $0.57 per share.

This prospectus supplement updates and supplements the information in the Prospectus and is not complete without, and may not be delivered or utilized except in combination with, the Prospectus, including any amendments or supplements thereto. This prospectus supplement should be read in conjunction with the Prospectus and if there is any inconsistency between the information in the Prospectus and this prospectus supplement, you should rely on the information in this prospectus supplement.

**Investing in our securities involves risks that are described in the *"Risk Factors"* section beginning on page 13 of the Prospectus.**

**Neither the SEC nor any state securities commission has approved or disapproved of the securities to be issued under the Prospectus or determined if the Prospectus or this prospectus supplement is truthful or complete. Any representation to the contrary is a criminal offense.**

**The date of this prospectus supplement is March 1, 2023.** 

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**UNITED STATES** 

**SECURITIES AND EXCHANGE COMMISSION** 

**WASHINGTON, D.C. 20549** 

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**FORM 8-K** 

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**CURRENT REPORT** 

**Pursuant to Section 13 or 15(d)** 

**of the Securities Exchange Act of 1934** 

**Date of Report (Date of earliest event reported): March 1, 2023** 

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## Astra Space, Inc.
**(Exact name of Registrant as Specified in Its Charter)** 

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| | | |
|:---|:---|:---|
| **Delaware** | **001-39426** | **85-1270303** |
| **(State or Other Jurisdiction**<br> **of Incorporation)** | **(Commission**<br> **File Number)** | **(IRS Employer**<br> **Identification No.)** |

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| | |
|:---|:---|
| **1900 Skyhawk Street**<br> **Alameda, California** | **94501** |
| **(Address of Principal Executive Offices)** | **(Zip Code)** |

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**Registrant's Telephone Number, Including Area Code: (866) 278-7217** 

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Check the appropriate box below if the Form 8-K filing is intended to simultaneously satisfy the filing obligation of the registrant under any of the following provisions:

☐ Written communications pursuant to Rule 425 under the Securities Act (17 CFR 230.425)

☐ Soliciting material pursuant to Rule 14a-12 under the Exchange Act (17 CFR 240.14a-12)

☐ Pre-commencement communications pursuant to Rule 14d-2(b) under the Exchange Act (17 CFR 240.14d-2(b)) 

☐ Pre-commencement communications pursuant to Rule 13e-4(c) under the Exchange Act (17 CFR 240.13e-4(c)) 

**Securities registered pursuant to Section 12(b) of the Act:** 

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| | | |
|:---|:---|:---|
| **Title of each class** | **Trading<br>Symbol(s)** | **Name of each exchange**<br> **on which registered** |
| Class A common stock, par value $0.0001 per share | ASTR | NASDAQ Global Select Market |

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Indicate by check mark whether the registrant is an emerging growth company as defined in Rule 405 of the Securities Act of 1933 (§ 230.405 of this chapter) or Rule 12b-2 of the Securities Exchange Act of 1934 (§ 240.12b-2 of this chapter).

Emerging growth company ☐

If an emerging growth company, indicate by check mark if the registrant has elected not to use the extended transition period for complying with any new or revised financial accounting standards provided pursuant to Section 13(a) of the Exchange Act. ☐

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| | |
|:---|:---|
| **Item 8.01** | **Other Events.**  |

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On March 1, 2023, Astra Space, Inc. (the "Company") published a blog post related to its receipt of the formal closure letter from the Federal Aviation Administration concluding the investigation involving LV0010 and sharing the Company's conclusions from the investigation. The blog post is available on the Company's website at www.astra.com. A copy of the blog post is included in this Current Report on Form 8-K as Exhibit 99.1.

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| | |
|:---|:---|
| **Item 9.01** | **Financial Statements and Exhibits.**  |

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(d) Exhibits

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| | |
|:---|:---|
| Exhibit<br>No. | Description |
| 99.1 | Blog post dated March 1, 2023 |
| 104 | Cover Page Interactive Data File (embedded with the Inline XBRL document) |

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**SIGNATURES** 

Pursuant to the requirements of the Securities Exchange Act of 1934, the registrant has duly caused this report to be signed on its behalf by the undersigned thereunto duly authorized.

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| | | |
|:---|:---|:---|
| Date: March 1, 2023 | Astra Space, Inc. | Astra Space, Inc. |
|  | By: | /s/ Axel Martinez |
|  | Name: | Axel Martinez |
|  | Title: | Chief Financial Officer |

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**Exhibit 99.1** 

***Conclusion of TROPICS-1 Mishap Investigation*** 

*By Andrew Griggs, Head of Mission Assurance, and Adam London, Founder and Chief Technical Officer* 

After over six months of rigorous testing and analysis, Astra has received a formal closure letter from the FAA concluding the TROPICS-1 mishap investigation. At this time, we'd like to share our conclusions from the investigation and lessons learned.

The TROPICS-1 mission launched on June 12, 2022 on Astra's Rocket 3.3, serial number LV0010. The rocket completed a nominal first stage flight, stage separation, and upper stage ignition. Shortly after the ignition of the upper stage engine, the upper stage's fuel consumption rate increased and remained anomalously high for the remainder of the flight. About 250 seconds after upper stage ignition, the stage exhausted its fuel supply with approximately 20% of the liquid oxygen still remaining onboard. As a result, the upper stage was only able to obtain about 80% of the required orbital velocity. The stage was unable to deliver its payloads to orbit, and subsequently re-entered the atmosphere, ending the mission.

Our analysis showed that the anomalous fuel consumption during the upper stage flight was due to a combustion chamber wall burn-through that occurred 18 seconds into upper stage flight. Flight data showed that the burn-through was precipitated by a substantial blockage of the fuel injector. The mechanics of combustion and regenerative cooling are complex and this failure did not have an immediately apparent root cause, so extensive testing and analysis was required to recreate the failure mode and to understand both how the injector blockage was created and how it led to a burn-through.

**About regenerative cooling** 

Let's begin with a quick primer on regenerative cooling. Most liquid rocket engines require cooling to prevent the very hot combustion gases from melting the chamber wall and causing the engine to fail. Rocket 3.3's upper stage engine used regenerative cooling to accomplish this. In a regeneratively-cooled rocket engine, cooling is achieved by routing the fuel through many cooling channels embedded within the combustion chamber wall. This allows heat from the wall to be absorbed into the flowing fuel, keeping the wall at a low enough temperature to prevent failure.

On TROPICS-1, a failure of the regenerative cooling system led to a chamber burn-through.

![LOGO](g388662img1.jpg)

*CAPTION: Schematic of regeneratively cooled rocket engine combustion chamber* 

**What caused the burn-through?** 

Astra concluded that the primary factor leading to the combustion chamber burn-through was a partial blockage of the injector. When the fuel injector is partially blocked, the rate of fuel passing through the cooling channels decreases. This reduces the amount of heat the fuel can absorb and makes the

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combustion chamber wall hotter. If the wall gets hot enough, the temperature of the wall can exceed the local boiling point of the fuel, causing some of the fuel to boil along the wall inside the channels. Sometimes this condition can "self-heal", because a small amount of boiling can actually enhance the cooling ability of the fuel, bringing the wall temperature back down. However, if too much of the fuel boils, its cooling capability is significantly and adversely impacted, and the wall temperature can go up and up until the wall fails and "burns through," dumping a portion of the fuel flow directly into the combustion chamber - essentially wasting it. This is what we determined had occurred during the TROPICS-1 launch.

In addition to the partial blockage of the injector, Astra determined that a secondary factor for the burn-through was thermal barrier coating erosion. Portions of the upper stage engine's combustion chamber have a thermal barrier coating on the inside to insulate the chamber wall and reduce the heat that the fuel is required to absorb as a coolant. If some thermal barrier coating is missing, even a very small amount, that portion of the wall can get much hotter and increase the likelihood of a local burn-through. During the investigation, Astra found that there was a small amount of missing thermal barrier coating on the LV0010 upper stage engine. This missing coating was in a location that was considered acceptable by engineers at the time, but further analysis showed that we had underestimated the need for coating in this region under flight conditions (more on the ground vs. flight differences in the next section).

**What caused the injector blockage?** 

While it was relatively straightforward to determine that a blockage of the injector had occurred during upper stage flight, it took much longer to conclusively determine what had caused the blockage. We used a combination of analysis and testing to systematically investigate each potential blockage source. Three credible sources for the blockage were the focus of this investigation:

&nbsp;&nbsp;&nbsp;&nbsp;&nbsp;&nbsp;&nbsp;&nbsp;&nbsp;&nbsp;• Foreign object debris ("FOD"), such as particles of metal

&nbsp;&nbsp;&nbsp;&nbsp;&nbsp;&nbsp;&nbsp;&nbsp;&nbsp;&nbsp;• Gaseous helium

&nbsp;&nbsp;&nbsp;&nbsp;&nbsp;&nbsp;&nbsp;&nbsp;&nbsp;&nbsp;• Gaseous fuel

After a review of flight results and testing to recreate the failure, we were able to conclude that the injector blockage was caused by a gas. This ruled out solid foreign object debris such as metal particles.

Next we examined helium, which is used for the upper stage's pneumatic and pressurization systems, and theoretically could have leaked into the fuel lines. We performed a barrage of tests on our pneumatic systems, attempting to cause helium to leak under flight-like conditions of vacuum, vibration, and low temperatures. We were unable to substantiate any meaningful leaks, nor did data from the LV0010 upper stage indicate any leaks before or during flight. The only other credible source of helium in the upper stage is in the pressurization system, found at the start of upper stage flight in a small "ullage" bubble at the top of the fuel tank. Analysis showed it is highly unlikely that this helium could migrate to the bottom of the tank and be ingested into the engine at the beginning of the burn. Even if it had migrated, it's even more unlikely that this helium could have remained in the bottom of the tank and sustained the injector blockage for the amount of time seen in flight (helium, since it's much lighter than fuel, tends to migrate toward the top of the tank as soon as the engine lights and the stage begins accelerating).

So, we were left with gaseous fuel as the main suspect. During ground acceptance testing, the fuel in the upper stage engine gets warm but we had never observed boiling or near-boiling within the cooling channels. However, the exhaust jet of the upper stage engine on the ground is "separated" from the inside of the engine nozzle by the pressure of the atmosphere around it, and therefore transfers less heat into the fuel. In flight, the engine is surrounded by vacuum and the exhaust jet expands to become "fully attached" to the inside of the nozzle. Therefore, the fuel passing through the engine during flight is heated to a higher temperature than during ground testing.

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![LOGO](g388662img2.jpg)

*CAPTION: Comparison of (ground) separated rocket engine flow vs (vacuum) fully-attached rocket engine flow* 

We conducted numerous experimental engine tests with fuel pre-heated to various temperatures to simulate the effect of full attachment. This allowed us to create a more sophisticated thermal model to predict the temperature of the fuel inside the engine with better accuracy than before. This analysis showed that, in flight, the fuel at the injector would have thin margins with respect to its boiling point. The most significant contributors to this thin margin were unique to the Rocket 3 architecture: a pressure-fed upper stage engine that operates at relatively low pressures, as well as the selection of a kerosene-like fuel with a higher vapor pressure than traditional rocket-grade kerosene (e.g. RP-1) to simplify testing and operations.

Given this thin margin, small factors - like the warm sunny weather in Cape Canaveral on the day of launch, which meant the fuel was slightly warmer than in prior flights - helped to tip the fuel over into a boiling regime on the TROPICS-1 mission. Our analysis has concluded that the boiling fuel caused the partial injector blockage in flight and, together with the eroded thermal barrier coating mentioned previously, caused a thermal "run-away" event that worsened the injector blockage and eventually led to the burn-through.

![LOGO](g388662img3.jpg)

*CAPTION: Upper stage engine testing shows streaks of molten metal from a hot wall burn-through event* 

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**Lessons learned** 

Almost immediately following the TROPICS-1 mishap, we made the strategic decision to focus the majority of Astra's resources on developing Astra's next-generation launch vehicle: Rocket 4. We focused the TROPICS-1 investigation on learning all that we could to inform the design and operation of this new, larger, and more reliable rocket. To that end, Rocket 4 incorporates key architectural choices (most notably, a different upper stage engine design and a different fuel) that completely eliminate the causes of this mishap. We have also introduced controls designed to eliminate a number of other potential failure modes (like FOD and helium ingestion) that the investigation concluded did *not* occur on the TROPICS-1 flight, but that Rocket 3.3 could have been susceptible to. For example, we are upgrading our helium diffuser design to prevent frothing in the propellant tanks and ingestion of helium into the engine.

In parallel with the technical cause investigation, Astra also conducted an internal investigation related to improving our processes, systems, and culture to increase the reliability of our fourth generation rocket. Astra has come a long way from the company that we were when we designed Rocket 3 back in 2018 and 2019; our team is now larger and more experienced, we have made significant investments in quality control and failure analysis, and we have learned vital lessons from both launch successes and failures. Still, we know that we have room to improve further, so we are implementing dozens of company-wide initiatives designed to ensure the reliability of Rocket 4. These improvements include an overhauled design review process, a more robust test-like-you-fly qualification process, and a refreshed set of Astra core values. I'm confident we now have the right team and systems in place to make Rocket 4 a success.

This was easily the most complex investigation that Astra has ever conducted. We were committed to rigorously and thoroughly investigating the cause of this mishap, and produced an incredible amount of analysis and test results to understand the failure and support our conclusions. Although we came to the preliminary conclusion of an injector blockage and a chamber burn-through quite quickly, we spent several additional months to ensure that we learned everything we could from this launch failure and left no stone unturned. I am thankful for the team's hard work and we are grateful for the support and partnership of NASA and the FAA throughout this process. We are putting these lessons into action as we prepare for the first launch of Rocket 4.